Deep Space Network - ission Suppo

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Deep Space Network

ission Suppo

Jet Propulsion Laboratory California institute of Technology

JPL 0-0787, Rev. AF

870-14, Rev. AF October 1991

Deep Space Network

ission Support Re uirements

Reviewed by:

L.M. McKinley TDA Mission Support Off ice

Approved by:

R.J. Amorose Manager, TDA Mission Support

Jet Propulsion Laboratory California Institute of Technology

JPL 0-0787, Rev. AF

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CONTENTS

INTRODUCTION ............................................................ A . PURPOSE AND SCOPE ................................................. B . REVISION AND CONTROL .............................................. C . ORGANIZATION OF DOCUMENT 870-14 ................................... D . ABBREVIATIONS ..................................................... ASTRO-D .................................................................

BROADCASTING SATELLITE-3A AND -3B (BS-3A AND -3B) ....................... CRAF/CASSINI (c/c) ......................................................

COSMIC BACKGROUND EXPLORER (COBE) .......................................

DYNAMICS EXPLORER-1 (DE-1) ..............................................

EARTH RADIATION BUDGET SATELLITE (ERBS) .................................

ENGINEERING TEST SATELLITE-VI (ETS-VI) .................................. EUROPEAN TELECOMMUNICATIONS SATELLITE I1 (EUTELSAT 11) ..................

EXTREME ULTRAVIOLET EXPLORER (EWE) ..................................... FRENCH DIRECT TV BROADCAST SATELLITE (TDF-1 AND -2) ..................... GALILEO .................................................................

GAMMA RAY OBSERVATORY (GRO) ............................................. 13-1

GEOSTATIONARY METEOROLOGICAL SATELLITE-5 (GMS-5) ........................ 14-1

GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITE (GOES I-M METSAT PROJECT) ......................................................... 15-1

GERMAN TELECOMMUNICATIONS SATELLITE (DEUTSCHER FERNMELDE SATELLIT) (DFS-1 AND DFS-2) ....................................................... 16-1

GIOTTO EXTENDED MISSION (GEMS) .......................................... 1 7 - 1

GOLDSTONE SOLAR SYSTEM RADAR (GSSR) ..................................... 18-1

HIPPARCOS ............................................................... 19-1

HUBBLE SPACE TELESCOPE (HST) ............................................ 20-1

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CONTENTS (contd)

INTERNATIONAL COMETARY EXPLORER (ICE) ................................... INTERNATIONAL SOLAR TERRESTRIAL PHYSICS (ISTP) PROGRAM .................. INTERNATIONAL SOLAR TERRESTRIAL PHYSICS (ISTP) GEOTAIL MISSION .......... INTERNATIONAL SOLAR TERRESTRIAL PHYSICS (ISTP) WIND MISSION ............. INTERNATIONAL SOLAR TERRESTRIAL PHYSICS (ISTP) POLAR MISSION ............ LANDSAT 4 AND 5 ......................................................... LASER GEODYNAMIC SATELLITE (LAGEOS 11) .................................. MAGELLAN ................................................................ MARS OBSERVER ........................................................... MUSES-A ................................................................. NIMBUS-7 ................................................................ OCEAN TOPOGRAPHY EXPERIMENT (TOPEX/POSEIDON) ............................ PIONEER 6 THROUGH 8 ..................................................... PIONEER 10 AND 11 .......................................................

PIONEER 12 (PN-12) ...................................................... 35-1

ROENTGENSATELLIT (ROSAT) ...............................................

SAMPEX ..................................................................

SOLAR-A ................................................................. SPACE FLYER UNIT (SFU) .................................................. SPACE TRANSPORTATION SYSTEM (STS) ....................................... TELECOM 2-A (TC2A) ...................................................... TELECOM 2-B (TC2B) ...................................................... TRACKING AND DATA RELAY SATELLITE SYSTEM (TDRSS) ........................ ULYSSES ................................................................. UPPER ATMOSPHERE RESEARCH SATELLITE (UARS) .............................. VOYAGER INTERSTELLAR MISSION (VIM) ......................................

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CONTENTS (contd)

APPENDIX A. DSN ADVANCED PLANNING MISSION SET. ....................... A-1

APPENDIX B. GLOSSARY. ................................................ B-1

APPENDIX C. DEFINITIONS OF TERMS ..................................... C-1

APPENDIX D. FACILITY IDENTIFIERS ..................................... D-1

DISTRIBUTION LIST ....................................................... DL-1

Figures

1. Mission Set ................................................. 1-2

Tables

A-1. Potential Future Missions ................................... A-1

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INTRODUCTION

A. PURPOSE AND SCOPE

The purpose of this document is to provide NASA and JPL management with a concise summary of information concerning the forecasting of the necessary support and requirements for missions described in this-publication.

This document presents a brief description of various missions along with specific support requirements for each. The missions described herein are those listed in the Mission Set prepared by the Mark IVA DSN Operations Planning group (see Figure 1). Figure 1 is presented here to provide the reader with a general overview o f the mission support requirements.

B. REVISION AND CONTROL

Revisions or changes to the information presented in this document may be initiated by all DSN personnel. The initiator should submit a written request for change to the TDA Mission Support and DSN Operations Manager Office.

Revisions, changes, and additions to this document will be issued on the first day of the first month of a calendar quarter.

C. ORGANIZATION OF DOCUMENT 870-14

This document describes each individual mission, which is titled and included in this document in alphabetical order. (Appendix A consists of a listing and description of various potential flight projects that are being investigated by JPL at the present time.)

D. ABBREVIATIONS

Abbreviations used in this document are normally defined at the first textual use of the technical term. Abbreviations and acronyms approved for use by the J P L Office of Telecommunications and Data Acquisition (TDA) are listed in Document 810-3, TDA Standard Practice - Glossary of Deep Space Network Abbreviations and Acronyms. Those not listed in Document 810-3, but used in this document, can be found in the Glossary (Appendix B) at the end of this document. The Glossary is followed by a listing of various terms and their definitions (Appendix C), which will assist readers who would like clarification of one or more of the terms used in this document. A list of facility identifiers and their definitions is contained in Appendix D.

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-a I c

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a P #- i

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ASTRO-D

TDS Mgr: J. Goodwin Project Mgr: Y. Tanaka (ISAS) NOPE: R. Nevarez G. W. Ousley, Sr. (GSFC)

MOM: K. Ninodya (ISAS)

Launch Date : February 1, 1993 Projected SC L ife/DSN Surmort : 2 years/2 years

project ResDonslbility: Institute of Space and Astronautical Science (ISAS) # . .

Source: TBS Sponsor: ISAS

A. MISSION DESCRIPTION

ASTRO-D, which is to be launched by a MU-311 vehicle, is a scientific Earth orbiting satellite of the Institute of Space and Astronautical Science (ISAS) of the Ministry of Education, Science, and Culture of Japan. Its mission is TBS.

B. FLIGHT PROFILE

ASTRO-D will be launched on a MU-311-5 launch vehicle from Kagoshima Space Center (KSC) in Uchinoura, Kagoshima Prefecture, Japan. Additional flight information is TBS.

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C. COVERAGE

No DSN lauch vehicle support is required. The DSN will support the Mission phase only.

1. Coverage Goals

The DSN will support 4 to 8 contacts per day depending on the Launch and Early Orbit phase (LEOP) and Mission phase, providing downlink telemetry recording only at all stations.

Additional coverage information is TBS.

2. Network Support

The support provided by the DSN is indicated in the following table :

Svstem

S-band TLM

S-band CMD

S-band TRK

NOTE: P = Prime

Goldstone Canberra Madrid

12 14 15 16 17 42 43 45 46 61 63 6 6

D. FREQUENCY ASSIGNMENTS

Frequencies are allocated according to the following table:

Svstem

S-band TLM

S-band CMD

S-band TRK

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E. SUPPORT PARAMETERS

The support parameters for the Telemetry, Command, and Support Systems are listed below:

(1 ) Telemetry

Data Streams 1 Format PCM (NRZ-S) BiO/PM or PCM (NRZ-S) PSK/PM Subcarrier Frequency 524000 Hz Bit Rates 1024, 4096, and 32768 b/s (Real-time)

Coding Convolutional, K=7 R=1/2 Record Required

131072 and 262144 b/s (Playback)

(2) Command

Format PCM (NRZ-L) /PSK/PM Subcarrier Frequency TBS Bit Rate 4000 b/s

(3) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Formats Rec o rdi ng o Analog o Digital

1 to 10 kW Moderate Required Required (26-m only) Modest N/A

N/A Required

F. TRACKING SUPPORT RESPONSIBILITY

The allocation of responsibility for tracking support is listed in the following table:

. . . . . Support Responsibilitv ission Phase

Prelaunch ISAS

Launch I SAS

LEOP & Mission DSN, ISAS

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BROADCASTING SATELLITE-3A AND -3B (BS-3A AND 3B)

(Reimbursable)

TDS Mgr: N. Fanelli NOPE: R. Nevarez

Project Mgr: K. Funakawa (NASDA) MOM: M. Horii (NASDA)

LV/Range: N-ll/TaSC

Launch Date: BS-3A: August 28, 1990; BS-3B: August 17, 1991 Prolected SC Life/DS N SUDDOrt : 5 years/7 to 30 days

Pro4ect ResDonsibilitv : National Space Development Agency, Japan (NASDA) . . I

Source: SIFUI Sponsor: NASDA

The Broadcasting Satellites-3A and -3B (BS-3A and -3B) are being planned and developed by Japan's National Space Development Agency (NASDA) as a follow-on to the BSE and BS-2 project that began in April 1978. The BS-3A and -3B will provide direct color TV boradcasting to the Japanese mainland and remote islands including the Okinawa and Ogasawara island groups. Control of the satellite will be from the Tsukuba Space Center.

B. FLIGHT PROFILE

The BS-3A and -3B satellites will be launched from Tanegashima Space Center (TaSC) in southern Japan by a type H-1 three-stage launch vehicle. The mission has been designed to follow the conventional injection sequence; i.e.,

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parking orbit, transfer orbit, and near-synchronous orbit. Attitude maneuvers will be performed to orient the spacecraft to the correct attitude prior to

' the Apogee Kick Motor (AKM) firing, which will occur at the 4th, 7th, 9th or 11th apogee. After AKM firing, drift phase orbital and attitude maneuvers will be performed to place the spacecraft at its final geostationary station posit ion.

C. COVERAGE

1. Coverage Goals

The coverage will consist of the 26-m antenna as prime and the Madrid 34-m antenna as backup support for the transfer and drift orbits. Maximum support will consist of'one 8-hour tracks per station for a 7-day period, plus 23 days of contingency support from all complexes.

2. Network Support

Svstem

S-band TLM

S-band CMD

Goldsto ne Canberra Madrid

12 14 15 16 17 42 43 45 46 61 63 66

S-band TRK P P B P

NOTE: B = Backup; P = Prime

3. Compatibility Testing

The BS-3A and -3B compatibility tests were completed in 1989 at JPL's compatibility test area (CTA-21) and include radio metric, telemetry, and command data flow.

Svstem Uplink ( MHz) Downlink (MHz) Polarization

S-band TLM -- 2280.721 RCP

RCP S-band CMD 2100.164 --

S-band TRK 2100.164 2280.721 RCP

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E . SUPPORT PARAMETERS

T h e support p a r a m e t e r s f o r the T e l e m e t r y , Command, and Support S y s t e m s a r e listed b e l o w :

(1) T e l e m e t r y

D a t a S t r e a m s F o r m a t PCM (SP-L) /PSK/PM Subcarrier Frequency 192 kHz B i t R a t e 512 b/s R e c o r d R e qu i red

(2) Command

F o r m a t PCM ( B i g - L ) PSK/PM B i t R a t e 1 25 G / s Subcarrier Frequency 1 6 kHz

( 3 ) Support

U p l i n k P o w e r A n t e n n a R a t e A n t e n n a A u t o t r a c k D o p p l e r R a t e s R a n g e F o r m a t R e c o r d i n g . A n a l o g . D i g i t a l

1 t o 1 0 kW Moderate T r a n s f e r - d r i f t o r b i t s Modest T o n e (100 kHz m a j o r )

R e q u i r e d N/A

T h e a l l o c a t i o n of responsibi l i t ies f o r t r a c k i n g support i s l is ted i n the f o l l o w i n g table:

I . ission Phase

L a u n c h T r a n s f e r / D r i f t O r b i t s G e o s t a t i o n a r y O r b i t s

T a S C DSN TACS (NASDA)

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CRAF/CASSINI (C/C)

TDS Mgr: R. Gillette NOPE: TBS

Project Mgr: J. Casani Deputy Project Mgr: R. Draper

Launch Date: Cassini - November 26, 1995 CRAF - February 10, 1996

projected SC Life/DSN SupDort: CRAF - 9.4 years Cassini - 12.6 years

project Responsibility: Jet Propulsion Laboratory , . .

Source: SIRD August 1991 Sponsor: OS0

CRAF (Comet Rendezvous Asteroid Flyby) - A mission to rendezvous with the comet Tempel 2 and to station-keep at the comet for a period of 2.6 years, including the comet perihelion. There is a flyby of the asteroid Mandeville prior to arrival at Tempel 2.

Cassini - A mission to place a spacecraft in a highly elliptical orbit around the planet Saturn and deliver a probe to the surface of its satellite Titan. There is a flyby of the asteroid 1989 UR1 prior to Saturn arrival.

Current Status - Congressional action on the Fiscal Year 1992 budget has cut funding for CRAF/Cassini, which will likely result in launch date changes. The next CRAF opportunity is a May 1997 launch to comet Kopff with arrival in late 2005. A likely Cassini launch would be October 1997 with arrival at Saturn in June 2004.

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B. FLIGHT PROFILE

1. CRAF

Launch

Maneuvers

Venus Grav i ty A s s i s t

A s t e r o i d Flyby

Ea r th Grav i ty A s s i s t

Comet Rende zvou s

P e r i h e l i o n

End of Mission

2. C a s s i n i

Launch

Maneuvers

Venus Grav i ty A s s i s t

Ea r th Grav i ty A s s i s t

A s t e r o i d Flyby 1989 UR1

J u p i t e r Grav i ty A s s i s t

Sa tu rn O r b i t I n s e r t i o n

Probe Sepa ra t ion

Probe En t ry

End of Mission

Ila.k!=

10 February 1996

6 November 1997, 1 November 1998, 18 September 2000, Others are TBD

28 A p r i l 1997

5 June 1998

25 February 1999

19 June 2000

1 6 February 2003

1 5 February 2005

31 June 2005

26 November 1995

9 J u l y 1998, 22 November 1998, Others are TBD

2 December 1996

5 J u l y 1998

7 January 1999

9 A p r i l 2000

25 June 2004

20 October 2004

12 November 2004

1 J u l y 2008

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C. COVERAGE GOALS

1. CRAF

The Project requires one tracking pass (plus one Delta VLBI pass) per week from the 34-m HEF stations during cruise periods, continuous 34-m HEF coverage from launch to L + 30 days and around gravity assists and maneuvers. Coverage from the 70-m is required during asteroid flyby, maneuvers, comet arrival and search. For a radio science experiment, continuous 34-m HEF and 70-m coverage is required for 30 days (March 20 through April 16, 2001).

2. Cassini

The Project requires one tracking pass (plus one Delta VLBI pass) per week from the 34-m HEF stations during cruise, continuous 34-m HEF coverage from launch to L + 30 days and around gravity assists and maneuvers. During Saturn orbital operations, one 34-m HEF pass per day for the 24 days of cruise-like activities, and continuous 34-m HEF support during the 6 days of high- level activities for each 30-day orbit are required.

3 . Additional Anticipated Coverage

Both CRAF and Cassini will use their Low Gain Antenna (LGA) during most of the first three years of cruise. While using the LGA, 70-m support will be required to support the low 5- and lO-b/s telemetry. If the 70-m subnet is not implemented with an X-band uplink capability, simultaneous 34-m coverage will be required to provide the uplink in order to meet the command and navigation requirements.

CRAF is an X-band uplink and downlink mission. Cassini will be X-band uplink with either X- or Ka-band downlink. Ka-band will not be supported until January, 2002. Cassini will also have an S-Band Radio Science downlink capability. X-band, Ka-band and S-band channel assignments are TBS.

The support parameters for these missions are:

1. Telemetry CRAF

Initial Acquisition Time 30 min Radio frequency X-band

Cassini

Same S-, X-, and Ka-band (S-band carrier only)

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Data rate 5 b/s t o 5 b/s t o 497.7 kb/s 497.7 kb / s

(X-band) , 169.5 (Ka-band)

S u b c a r r i e r f requency 22.5 kHz, 360 kHz Same Coding

Convolu t iona l K-15 , R=1/6 Same Reed-Solomon J=E,E=16,1=5 Same

Command

Radio frequency X-band Same D a t a ra te 7.8125 t o 5 0 0 b/s Same S u b c a r r i e r f requency 16 kHz Same S u b c a r r i e r waveform s inewave Same Coding PSK/NRZ-L Same P o w e r (emergency suppor t ) 20 kW on 70m o r Same

80 kW on 3 4 m ( Jan . , 2000)

Navigat ion

Doppler, ranging, wide-band Required and narrow-band VLBI

Radio Sc ience

Open-loop (nea r - r ea l t i m e ) Required Closed-loop ( r e a l t i m e ) Required

Required

Required Required

Monitor

R e a l - t i m e s t a t i o n data Required Required

The DSN is r e s p o n s i b l e f o r a l l suppor t f o r bo th CRAF and Cass in i , i n c l u d i n g prelaunch checkout a t CTA 21 and MIL 71.

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IC BACKGROUND EXPLORER (COBE)

(Emergency Support)

TDS Mgr: N. A . Fanelli NOPE: R. E. Nevarez

Project Mgr: R. Mattson MOM: R. Stanford

LV/Range: Delta 592O/WTR

Jlaunch Date: October 15, 1989 (Launched November 1989) Projected SC TIife/DSN Support: 1 year/l year

Proiect ResDonsIbilitv: Goddard Space Flight Center (GSFC) . a .

Source: SIRD Sponsor: OS0

A . MISSION DESCRIPTION

The Cosmic Background Explorer (COBE) Mission will measure the diffuse radiation from the universe in the wavelength band 1 micron to 9.6 mm. The band includes the 3OK cosmic background radiation, the known relic of the primeval cosmic explosion. It is also expected to contain the radiation produced at the time of the formation of the first galaxies or stars in the universe. The mission will provide the most comprehensive observations to date of the radiative energy content of the universe, a data set essential for the further iteration of theory and observation in cosmological research.

B. FLIGHT PROFILE

The COBE satellite will be launched from the Western Space and Missile Center (EWSMC) via the Delta into a circular parking orbit of about 300 km. COBE will be placed into a 900-km altitude circular orbit.

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C. COVERAGE

1. Coverage Goals

Coverage will be provided by the DSN for COBE emergencies that would prevent communications via the normal channels of TDRSS. Emergency support will be provided by the DSN 26-meter subnetwork.

2. Network Support

The support provided by the DSN is indicated in the following table:

Svstem Goldsto ne Canberra Madrid

12 14 15 16 42 43 45 46 61 63 66

S-band TLM E E E

S-band CMD E E E

S-band TRK E E E

NOTE: E = Emergency Support

Svstem m i n k (MHz) Downlink (MHz 1 Polarization

S-band TLM -- 2287.5 LCP

LCP S-band CMD 2106.4 --

S-band TRK 2106.4 2287.5 LCP

(1) Telemetry

Data Streams 2

Format PCM/PSK/PM B i 0 - L Subcarrier Frequency 1024 kHz Bit Rates 1000, 4096, 655.36 kb/s Coding Convolutional Record Analog

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(2) Command

Format Bit Rate Subca r rie r Frequency Subcarrier Waveform

(3) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Format Recording . Analog . Digital

PCM/PSK/PM 2000 Hz 16000 Hz Sine

Up to 2 kW Mode rat e Required Yes Up to 70 Hz/s Sine

Yes No

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DYNAMICS EXPLORER4 (DE-I)

Project Mgr: P. Pashby (GSFC) MOM: F. Gordon (GSFC)

LV/Range: Delta 3913/WTR

Launch Date: August 3, 1981 Projected SC Life/DSN Surmort: 12 years/9 years

Project ResDonsibility: Goddard Space Flight Center (GSFC) I , ,

Source: SIRD June 28, 1983 Sponsor: OS0

The Dynamics Explorer (DE) mission is designed to study the Earth's electromagnetic fields at varying heights up to 4 Earth radii.

B. FLIGHT PROFILE

The DE-1 was launched on a Delta 3913 launch vehicle from the Western Test Range (WTR) and was placed in a 561 x 23279 km orbit with a 90-degree inclination. The orbital period is approximately 439 minutes.

C. COVERAGE

The DSN began to support this GSFC extended mission on February 1, 1985.

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1. Coverage Goals

Coverage c o n s i s t s of f i v e passes per day t h a t l a s t f o r 45 minutes each.

2. Network Support

The suppor t p rovided by t h e DSN i s i n d i c a t e d i n t h e fo l lowing table :

Svstem

S-band TLM

S-band CMD

12 1 4 1 5 1 6 42 4 3 45 46 61 63 66

S-band TRK P P P

NOTE: P = Prime

D . FREQUENCY ASSIGNMENTS

Frequencies are a l l o c a t e d accord ing t o t h e fo l lowing table:

Svstem u ! J H Downlink ( M H d P o l a r i z a t i o n

S-band TLM -- 2214.0 L inea r

TBD -- S-band CMD 2038 I 725

S-band TRK 2038.725 2214.0 TBD

The suppor t parameters f o r t h e Telemetry, Command, and Support Systems are l is ted below:

(1) Telemetry

D a t a Streams 2 Format PCM/PSK/PM + PCM/PM o r Analog/PM S u b c a r r i e r Frequency 768 kHz B i t R a t e 1.024 t o 131.072 kb/s Record Required

(2) Command

Format PCM/PSK/PM B i t R a t e 1 0 0 0 b/s S u b c a r r i e r Frequency 16 kHz

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( 3 ) Support

Nominal 2 kW Moderate Required Not required Modest Tone (500 kHz major tone)

Required Not required

The allocation of responsibilities for tracking support is listed in the following table:

* . 8 . . ission Phase ort Responsibility

Delta 3913 Launch Earth Orbit

WTR GSTDN until Feb. 1985 DSN after Feb. 1985

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EARTH RADIATION BUDGET SATELLITE (ERBS)

(Emergency Support)

TDS Mgr: N. A . Fanelli NOPE: R. E. Nevarez

Project Mgr: P. Pashby (CSFC) MOM: J. Williamson (CSFC)

LV/Range: Delta/WTR

Launch Date: October 5, 1984 Proiected SC L ife/DSN SUpDOrt : 7 years/7 years

Project ResDo : Goddard Space Flight Center nsibilitv 6 . .

Source: SIRD May 1982 Sponsor: OS0

The primary purpose of the Earth Radiation Budget Satellite (EMS) project is to study the Earth's atmospheric processes and their relationship to the Earth's climate.

B. FLIGHT PROFILE

The ERBS satellite was launched by the STS shuttle. Following deployment from the shuttle, a hydrazine propulsion system maneuvered the satellite into a circular orbit. Orbit parameters are: 610 km x 610 km x 57 degrees, with a period of 99.6 minutes.

The ERS spacecraft was launched in 1984 from the Western Test Range (WTR) on a two-stage Delta launch vehicle and placed into a constant local time circular orbit with a nominal altitude of 610 km and an inciination of

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57 deg. This project support is expected to be ongoing for a minimum of 7 years

C. COVERAGE

1. Coverage Goals

The DSN will support ERBS during emergency situations in the event the standard TDRSS to White Sands data link is inoperative. Emergency support will be provided by the DSN's 26-meter antenna subnetwork.

2. Network Support

Svstem Goldstone Canberra Madrid

12 14 15 16 42 43 45 46 61 63 66

S-band TLM

S-band CMD

S-band TRK

NOTE: E = Emergency

Frequencies are allocated accordin to the followi

Svstem Uplink (MHz) Downlink (MHz)

S-band TLM -- 2287.5

S-band CMD 2106.4 --

S-band TRK 2106.4 2287.5

g table :

Polarization

E. SUPPORT PAMETERS

The support parameters for the telemetry, command, and support systems are listed below:

(1 1 Telemetry

Data Streams 2 Format PCM/PSK/PM Subcarrier Frequency 1024 kHz

Bit Rates Coding Record

(2) Command

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Format Subcarrier Frequency Bit Rate

(3) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range orm mat Recording . Analog . Digital

1.0, 1.6, 12.8, 32, or 128 kb/s Bi 0 -L Analog

PCM' (NRZ-L) PSK/PM 16 kHz 1 kb/s

2 kW Moderate Required Required Required SINE

Required Not required

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ENGINEERING TEST SATELLITE VI (ETS-VI)

TDS Mgr: J. Goodwin NOPE: R. Nevarez

Project Mgr: K. Funakawa (NASDA) MOM: M. Horii (NASDA)

Tlaunch Date: August 1993 Projected SC Life/DSN Support: 10 years/lO days

proinct Responsibilitv: National Space Development Agency, Japan (NASDA) * I ,

Source: SIRD June 1989 Sponsor: NASDA

The Engineering Test Satellite-VI (ETS-VI) is being developed by the National Development Agency of Japan (NASDA) as the third Japanese three-axis stabilized engineering test satellite to establish the 2-ton geostationary operational satellite bus system and to demonstrate the high performance satellite communication technology for future operational satellites. The satellite is to be stationed at 154 deg east longitude. The mission life is expected to be 10 years.

B. FLIGHT PROFILE

The ETS-VI satellite will be launched from Tanegashima Space Center (TaSC) in southern Japan by a type H-I1 launch vehicle. The mission has been designed to follow the conventional injection sequence into synchronous orbit

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v i a pa rk ing o r b i t , t r a n s f e r o r b i t , and d r i f t o r b i t . The sequence i n t r a n s f e r o r b i t r e q u i r e s f i r i n g t h e l i q u i d Apogee Engine t h r e e t i m e s t o raise t h e perigee of t h e t r a n s f e r o r b i t t o t h e g e o s t a t i o n a r y a l t i t u d e . A t t i t u d e maneuvers w i l l be performed t o o r i e n t t h e s p a c e c r a f t t o t h e c o r r e c t a t t i t u d e p r i o r t o t h e Apogee Engine F i r i n g (AEF), which w i l l occur a t t h e 2nd, 6 th , and 7 t h apogee. A f t e r AEF d r i f t phase o r b i t a l and a t t i t u d e maneuvers w i l l be performed t o p l a c e t h e s p a c e c r a f t a t i t s f i n a l g e o s t a t i o n a r y p o s i t i o n ,

C. COVERAGE

The DSN w i l l suppor t t h e pre launch c o m p a t i b i l i t y test , data i n t e r f a c e v e r i f i c a t i o n t e s t i n g , and launch r e h e a r s a l s . The DSN primary suppor t p e r i o d i s from launch through t h e f i n a l AEF p l u s 1 hour. Contingency suppor t i s from f i n a l AEF p l u s 1 hour u n t i l launch p l u s 1 month.

1. Coverage Goals

The coverage w i l l c o n s i s t of a l l t h e 26-m an tennas a s p r i m e and t h e 34-m antennas a t Madrid and Canberra as backup through t h i s suppor t . Maximum suppor t w i l l c o n s i s t of two 8-hour t r a c k s per s t a t i o n f o r a 7-day per iod , p l u s t h e cont ingency suppor t , i f r equ i r ed .

2. Network Support

The suppor t p rovided by t h e DSN i s i n d i c a t e d i n he fo l lowing t a b l e :

12 1 4 15 16 42 43 45 46 6 1 63 66

S-band TLM P B P B P

S-band CMD P B P B P

S-band TRK P B P B P

NOTE: P = P r i m e B = Backup

Svstem Uplink [MHz) 2 o l a r i z a t i . a

S-band TLM N/A 2212.000 RCP

S-band CMD 2036.883 N/A RCP

S-band TRK 2036.883 2212.000 RCP

870-14, Rev. AF

(1) Telemetry

Data Streams 1 Format PCM (SP-L) /PM Subcarrier Frequency TBS Bit Rates 512 b/s Coding N/A Record Required

(2) Command

Format PCM (NRZ-L) /PSK/PM Subcarrier Waveform Sine Subcarrier Frequency 16 kHz Bit Rate 1000 b/s

( 3 ) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Formats

Recording . Analog . Digital

1 to 10 kW Mode rat e Required Required (26-m Only) Modest Tone (Prime) (100 kHz Major Tone) DSN Standard (Backup)

N/A Required

The allocation of responsibility for tracking support is listed in the ~ following table:

Launch TaSC

Transfer/Drift Orbits DSN

Geostationary Orbit

Contingency

TACC (NASDA)

DSN (on request)

870-14, Rev. AF

870-14, R e v . AF

EUROPEAN TELECOMMUNICATIONS SATELLITE II (EUTELSAT II)

(Reimbursable)

TDS M g r : N . F a n e l l i NOPE: R. Nevarez

P r o j e c t M g r : P. B r i t t i n g e r (GSOC) MOM: G. L a e m e l (GSOC)

LV/Range: Ariane/CSG

Launc h Da te : F-1 August 30, 1990; F-2 January 15, 1991; F-3 August 8, 1991;

P r o j e c t e d SC L ife/DSN SupDort : 7 years / lO days F-4 January 15, 1992; F-5 Ju ly 15, 1992, F-6 January 15, 1993

0 & r-q-42 Q / ,%"+! I

P r o i e c t ResDons ib i l i tv : Research Agency f o r Aerospace Technology, Germany (DLR)

Source: SIRD (Rev. 5) J u l y 1989 Sponsor: DLR

EUTELSAT I1 i s a r e g i o n a l p u b l i c telecommunications system f o r Europe. The services which w i l l be provided a r e te lephone and t e l e v i s i o n .

EUTELSAT i s a European telecommunication sa te l l i t e o r g a n i z a t i o n created i n 1977 by 17 m e m b e r states of t h e European Conference of P o s t a l and T e l e c o m - municat ions Adminis t ra t ions (CEPT) which now is comprised of 26 m e m b e r states.

The satell i tes w i l l be placed a t a g e o s t a t i o n a r y o r b i t w i t h i n t h e arcs 6 degrees east t o 19 degrees e a s t o r 26 degrees east t o 36 degrees east . The des igned l i f e t i m e i s 7 y e a r s .

870-14, Rev. AF

B. FLIGHT PROFILE

EUTELSAT I1 satellites will be launched using one of the following launch vehicles: Ariane 4, Titan, or Atlas G Centaur depending on their availability.

After separation of the satellites from the launch vehicle, telemetry, telecommand, and ranging will be performed within S-Band frequencies. After positioning of the satellite at its final geostationary orbit the Ku-Band telecommunication equipment will be activated. From this time on all satellite control operations will be performed in Ku-Band. S-Band will only be reactivated in case of emergency.

C. COVERAGE

The DSN will support the transfer and drift orbit mission phases.

1. Coverage Goals

The coverage will consist of the 26-m antennas at Goldstone and Canberra as prime support for the transfer and drift orbits. Maximum support will consist of a 7-day period, plus 14 days of contingency support.

2. Network Support

Svstem Goldsto ne Canberra Madrid

12 14 15 16 17 42 43 45 46 61 63 66

S-band TLM P B B P B B

S-band CMD P B B P B B

S-band TRK P B B P B B

,NOTE: P = Prime B - Back-up

CTA 21 will support compatibility testing with the EUTELSAT TT&C "suitcase" model at approximately launch minus 11 months. These tests will verify and test the spacecraft RF compatibility with the DSN.

870-14, R e v . AF

Frequencies a r e a l l o c a t e d according t o t h e followi’ng table:

Svstem Uplink { M W

S-band TLM -- 2264.6250

S-band CMD 2085.3420 --

S-band TRK 2085.3420 2264.6250

p o l a r i z a t i o n

The suppor t parameters f o r t h e Telemetry, Command, and Support Systems a r e l i s ted below:

(1) Telemetry

D a t a Streams 1 Format PCM (NRZ-L) /PSK/PM S u b c a r r i e r Frequency 32768 H z B i t Rate 512 b / s Record Required

(2) Command

Format PCM (NRZ-L) /PSK/PM B i t R a t e 5 0 0 b /s S u b c a r r i e r Frequency 8000 Hz

( 3 ) Support

Uplink Power Antenna R a t e Antenna Angle Data Antenna Autotrack Doppler Rates Range Format

Recording . Analog . D i g i t a l

1 t o 1 0 kW Moderate Required Required (26-m antenna, on ly) Modest Tone (Prime) ( 1 0 0 kHz major t one ) DSN s t a n d a r d (Backup)

Required R e q u i r e d f o r 34-m backup

870-14, Rev. AF

4 . . . I Phase Dort ResDonslhla&

Ariane Launch Transfer/Drift Orbits Geostationary Orbit

CSG DSN DFVLR

870-14, Rev. AF

EXTREME ULTRAVIOLET EXPLORER (EUVE)

(Emergency Support)

TDS Mgr: N. A. Fanelli NOPE: R. E. Nevarez

Project Mgr: J. Barrowman (GSFC) MOM: H. Zayas (GSFC)

LV/Range: Delta/ETR

Launch Date: January 18, 1992 Proiected SC L ife/DSN SuoDort : 2 4 month413 months

Proiect Reswns ibilitv : Goddard Space Flight Center (GSFC)

Spurce: SIRD Draft Sponsor: NASA

The Extreme Ultraviolet Explorer (EWE) will conduct a survey of the entire celestial sphere in the extreme ultraviolet (W) spectrum, 100 to 1000 angstrom units. This survey will be accomplished using four grazing incidence telescopes mounted on a spinning spacecraft whose spin axis is along the Sun line. The axes of three telescopes sweep out a circle perpendicular to the Sun line for each revolution of the spacecraft. The fourth telescope points in the anti-solar direction. Data is taken only when the spacecraft is in the Earth's shadow.

B. FLIGHT PROFILE

The E W E will be placed into a near-circular orbit by a Delta expendable launch vehicle.

870-14, Rev. AF

The des ign o r b i t is c i r cu la r a t an a l t i t u d e of 550 km by 28.5 degrees f o r a p e r i o d of 96 minutes .

The E W E w i l l be flown on a standardized Explorer P la t fo rm (EP) which w i l l be reused f o r followup e x p l o r e r miss ions . The EP i s a new Mult imission Spacec ra f t (MMS) .

C. COVERAGE

1. Coverage Goals

Coverage w i l l be provided by t h e DSN f o r E W E emergencies t h a t would prevent communications v i a t h e normal channels of t h e Tracking and D a t a Relay S a t e l l i t e System (TDRSS). Emergency suppor t w i l l be provided by t h e 26- m e t e r subnet .

2. Network Support

The suppor t provided by t h e DSN i s indicated i n t h e fo l lowing table :

1 2 1 4 1 5 1 6

E S-band TLM

S-band CMD

S-band TRK

NOTE: E = Emergency Support

42 43 45 46

6 1 63 66

Frequencies are a l l o c a t e d accord ing t o t h e fo l lowing table:

S-band TLM 2287.5

S-band CMD 2106.4

S-band TRK 2106.4

2287.5

The suppor t parameters f o r t h e Telemetry, Command, and Support Systems are listed below:

870-14, R e v . AF

D a t a S t r e a m s F o r m a t s Subcarrier f requencies B i t R a t e s C o d i n g R e c o r d

(2) Command

F o r m a t B i t R a t e Subcar r ie r Frequency

(3) Support

U p l i n k P o w e r A n t e n n a R a t e A n t e n n a A n g l e R a t e A n t e n n a A u t o t r a c k D o p p l e r R a t e s R a n g e F o r m a t R e c o r d i n g . A n a l o g . D i g i t a l

2 TBD 1 0 2 4 k H z 384 b/s , 1 6 k b / s

A n a l o g

PCM (NRZ-L) PSK/PM 2 k b / s 1 6 kHz

U p t o 2 kW H i g h R e q u i r e d R e q u i r e d TBD S i n e

Y e s N o

870-14, Rev. AF

870-14, Rev AF

FRENCH DIRECT TV BROADCAST SATELLITE

(TDF-1 AND -2)

(Reimbursable)

NSM: N. Fanelli NOPE: R. Nevarez

Project Mgr: A. Pouzet (CNES)C) MOM: R. Vacheyroux (CNES)

LV/Range: ArianefCSG

Jlaunch Date: TDF-1: Launched October 27, 1988; TDF-2: Launched July 24, 1990 Projected SC Life/DSN SUDDOrt : 8 years/30 days

Proiect Responsibilitv: Centre National d'Etudes Spatiales (CNES) . I ,

Source: SIRD (Rev. 1) October 1989 Sponsor: CNES

The French Direct TV Broadcast Satellite (TDF-1 and -2) missions are to provide three channels of TV and sound broadcasting to France within the 12 to 18 GHz bands. The satellites will be placed in a geostationary orbit at 19 degrees west longitude.

B. FLIGHT PROFILE

TDF-1 and -2 will be launched from the Centre Spatial Guyanis in French Guiana on an Ariane launch vehicle. The missions follow the typical injection sequence; i.e., parking orbit, transfer orbit, and drift orbit. Attitude maneuvers will be performed to orient the spacecrafts prior to Apogee Kick Motor (AKM) firing. After AKM firing, drift phase orbital and attitude maneuvers will be performed to place the spacecrafts in their final geostationary position.

870-14, Rev AF

C. COVERAGE

1. Coverage Goals

The coverage will consist of the 26-m antennas at Goldstone and Canberra as prime support for the transfer and drift orbits. Maximum support will consist of two 8-hour tracks per station for a 7-day period, plus 14 days contingency support.

2. Network Support

12 14 15 16 42 43 45 46 61 63 66

S-band TLM

S-band CMD

S-band TRK

NOTE: P = Prime

CTA 21 will support spacecraft compatibility testing with the TDF-1 Telemetry, Tracking, and Command (TTtiC) "suitcase" model at approximately launch minus 6 months. These tests will verify and test the spacecraft RF compatibiliby with the DSN.

Svstem Uplink (MHzl Downlink (MHz) Polarization

S-band TLM

S-band CMD

S-band TRK

-- 2204.73

2030.189 --

2030.189 2204.73

870-14, Rev AF

(1) Telemetry

Data Streams 1 Format PCM (SP-L) /PSK/PM Subcarrier Frequency 32768 Hz Bit Rate 512 b/s Record Required

(2) Command I '

Format PCM/PSK/PM Bit Rate 500 b/s Subcarrier Frequency 8000 Hz

(3) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Format

1 to 10 kW Mode rat e Required Required Modest Tone (Prime), (100 kHz major tone) DSN standard (Backup)

Required Required for 34-m backup

Support Responsibility I . . Mission Phase

Ariane Launch Transfer /D ri f t Orbits Geostationary Orbit

CSG D SN CNES

870-14, Rev AF

870-14, Rev. AF

GALILEO

TDS Mgr: P. E. Beyer NOPE: R. O’Connor

Project Mgr: W. J. O’Neil Mission Director: N. E. Ausman

LV/Range: STS-IUS/ETR

Launch Date : October 18, 1989 Projected SC Life/DS N S u p -01%: 10 years/lO years

Source: SIRD May, 1988; NSP November, 1988 Sponsor: O S 0

The purpose of the Galileo missions is to make observations of Jupiter and its satellites using an orbiting spacecraft and an atmospheric entry probe. The mission will determine the chemical composition and physical state of the Jovian atmosphere and its satellites, and the topology and behavior of the magnetic field and energetic particle flux of Jupiter.

B. FLIGHT PROFILE

The current Galileo Mission Plan calls for a Venus Earth Earth Gravity Assist (VEEGA) trajectory having a launch to end-of-mission duration of approximately 8 years.

The Galileo spacecraft consisting of an Orbiter and a Probe, together with an Intertial Upper Stage (IUS), was placed in Earth orbit by the Space

870-14, Rev. AF

Transportation System (STS) on October 18, 1989. The IUS placed the spacecraft on a trajectory to encounter Venus (20,000-km altitude) on February 10, 1990. The first Earth encounter (1000-km altitude) occurred on December 8, 1990. A second Earth encounter occurring on December 8, 1992 at 300-km altitude will establish the final trajectory to Jupiter with arrival date of December 7, 1995.

The Probe will be released 150 days prior to Jupiter arrival and will enter the Jovian atmosphere at just prior to JOI. During descent, the Probe will transmit its telemetry data directly to the orbiter for playback to Earth as soon as possible thereafter.

Following J O I , the orbiter will commence a 22-month, 10-satellite tour to complete the mission by July 1997.

C. COVERAGE

1. Coverage Goals

The current (1/91) estimate of the antenna coverage profile is given below. IOM GLL-MDT-90-141 is the basis for the updates to the profile as defined in the SIRD. This profile reflects the changes induced by the actual launch on 18 October 1989. Such changes include time of oppositions and conjunctions, size and locations of maneuvers, and a more comprehensive understanding of spacecraft performance. This will be refined as the actual mission design progresses. Note that the support rate is given in passes per month (ppm) for all mission phases, even though the duration of several phases is much less than one month.

a . ission Phase

(a) Launch

(b) Cruise

(c) Venus Encounter

(d) Cruise

(e) Earth Encounter 1

Period Passes/Month

10/89 10/89 5 5 39

11/89 12/89 88

1/90 2/90 3 56

3/90 10/90 2 40

11/90 12/90 6 6 80

(f) Cruise 1/91 9/91

(g) Gaspra Encounter 10/91 11/91

Antennas

2 6m 34 STD 7 Om

34 STD 7 Om

2 6m 34 STD 7 Om

34 HEF 7 Om

870-14, Rev. AF

ission Phase Passes/ Month Antennas Period a .

Conjunction 1

Cruise Science

Earth Encounter 2

Cruise Science

Opposition 3

Cruise Science

Opposition 4, Gravity Wave

Cruise Science

Probe Release, Opposition 5

Pre JOI

(t) Pre JOI

(u) Jupiter Orbit Insertion

(v) Tour

10/95 10/95

11/95 12/95

1/96 10/97

16 70 6

3 9 28

6 90 90

90 90 90

28 15 50

34 HEF 7 Om

34 HEF 7 Om 2 6m

34 HEF 7 Om

34 HEf 7 Om

34 HEF 7 Om

34 BWG 34 HEF 7 Om

34 BWG 70 34 HEF 70 70m

34 BWG 34 HEF 7 Om

870-14, Rev. AF

2. Network Support

DSN support will be provided as indicated in the following table:

12 14 15 16 42 43 45 46 61 63 66

S-band TLM P P * P P P P *

X-band TLM P P P P P P P P

S-band CMD P P * P P P P *

X-band CMD P P

S-band TRK P P P * P P P P *

X-band TRK P P P P

NOTE: P = Prime; * = 26-m S-band support for near-Earth support Only.

3. Prelaunch System Tests

Prelaunch and system testing was supported by MIL 71.

Svstem Uplink (MHz) Downlink MHz) Polarization

S-band TLM -- 2295.0/2296.5 Linear/RCP*

X-band TLM -- 8415.0/8420.4 RCP

S-band CMD 2114.7 (Prime) 2113.3 (Spare)

RCP * .-

RCP X-band CMD 7166.9 --

Svstem Uplink (MHz) Downlink (MHz 1 Polarization

S-band TRK 2114.7 2296.5 Linear/RCP*

X-band TRK 7166.9 (Prime) 7162.3 (Spare)

8420.4 RCP

Note: *S-band HGA equals Linear S-band LGA equals RCP

870-14, Rev. AF

(1) Telemetry

Data Streams Format Subcarrier Frequency Bit Rate

Record Coding

(2) Command

Format Bit Rate Subcarrier Frequency

(3) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates

Range Format Recording . Analog . Digital . VLBI

The allocation of responsibilities following table:

STS Launch (complete) IUS Injection (complete)

2 PCM(NRZ) /PSK/PM 22.5, 360 kHz 10, 40, 1200 b/s 7.68, 168, 28.8, 67.2, 80.64, 115.2, 134.4 Kb/s Required Convolutional, K=7 R=1/2; K=15 R=1/4 (115, 134.4 Kb/s only)

PCM (Manchester encoded) /PSK/PM 32 b/s 512 Hz

10 to 125 kW Sidereal, except at launch Not required First pass (26-m autotrack) Moderate, except first pass and encounter Standard DSN

Not required Required AD OR

for tracking support is listed in the

TDRS S RTS

Cruise/Planetary (in progress) DSN

870-14, Rev. AF

W M . - - FT

(1:") (1 870-14, Rev. AF ,,f

GAMMA RAY OBSERVATORY (GRO)

(Emergency Support)

Project Mgr: J. Madden (GSFC) MOM: K. Schauer (GSFC)

LV/Range: STS/ETR

Launch Date: November 1, 1990 Projected SC Life/DSN Support : 2 years/2 years

Project Respons ibilitv: Goddard Space Flight Center

Source: SIRD January 1983 Sponsor: O S 0

The Gamma Ray Observatory (GRO) is an Earth orbiting satellite that studies sources of localized, galactic, and extragalactic gamma rays.

B. FLIGHT PROFILE

The GRO satellite will be carried into a near-circular orbit by the STS shuttle. Following launch from the shuttle, it will be placed in its operational orbit by the on-board hydrazine propulsion system. Formal orbit parameters are 350 km x 450 km x 28.5 degrees with a period of 93 minutes.

C . COVERAGE

8 7 0 - 1 4 , R e v . AF

1. C o v e r a g e G o a l s

DSN coverage f o r t h e GRO w i l l be provided dur ing e m e r g e n c i e s t h a t w o u l d prevent c o m m u n i c a t i o n s v ia t h e normal TDRSS-Whi te Sands l i n k . E m e r g e n c y support w i l l be provided by t h e D S N ' s 26-meter antenna s u b n e t w o r k .

2 . N e t w o r k Support

T h e support provided by t h e DSN i s indicated i n t h e f o l l o w i n g t ab le :

1 2 14 15 1 6 4 2 4 3 4 5 4 6 6 1 63 66

S-band TLM E E E

S-band CMD E E E

S-band TRK E E E

NOTE: E = E m e r g e n c y

Frequencies a re allocated according t o t h e f o l l o w i n g t ab le :

Svstem U D l i n k C M H a l D o w n l i n k (MHz 1 Pol a r Fz a t i on

S-band TLM -- 2287.5 TBD

TBD S-band CMD 2 1 0 6 . 4 --

S-band TRK 2 1 0 6 . 4 2287.5 TBD

T h e support p a r a m e t e r s f o r t h e t e l eme t ry , command, and support s y s t e m s are listed b e l o w :

D a t a S t r eams 2 F o r m a t TBD Subcar r ie r Frequency 32768 Hz B i t R a t e s 1, 32, o r 512 kb/s C o d i n g TBD R e c o r d TBD

870-14, R e v . AF

( 2 ) C o m a n d

F o r m a t S u b c a r r i e r Frequency B i t R a t e

(3) Support

U p l i n k P o w e r A n t e n n a R a t e A n t e n n a A n g l e D a t a A n t e n n a A u t o t r a c k D o p p l e r R a t e s R a n g e F o r m a t R e c o r d i n g . A n a l o g . D i g i t a l

PCM(NRZ-L) PSK/PM 1 6 kHz 125 G / s o r 1 kb/s

TBS TBS R e q u i r e d R e q u i r e d TBS TBS

870-14, Rev. AF

TATIONARY METEOROLOGICAL &tee 8 SATELLITE-5 a"

(GMS-5)

(Reimbursable)

&tee 8 SATELLITE-5 a"

(GMS-5)

(Reimbursable)

TDS Mgr: J. Goodwin NOPE: R. Nevarez

Project Mgr: TBS MOM: M. Horii (NASDA)

Launch Date: 1 January 1994 Projected SC Life/DSN Suppo rt: 7 years/lO days

project Responsibilitv: National Space Development Agency, Japan (NASDA)

Source: TBS Sponsor: NASDA

A MISSION DESCRIPTION

The Geostationary Meteorological satellite (GMS-5) which is being developed by the National Space Development Agency of Japan (NASDA) is the fifth geostationary, spin stabilized, weather satellite. Its purposes are observation of cataclysmic events such as hurricanes, typhoons, and regional weather phenomena; day and night observations of regional weather; relay of meteorological observation data from surface collection points (ships, buoys and weather stations) to the Data Processing Center in Japan; and transmission of processing imaging data for facsimile reproduction of distribution points in the Western Pacific area.

B. FLIGHT PROFILE

The GMS-5 satellite will be launched from Tanegashima Space Center (TaSC) in southern Japan by a type H-I1 launch vehicle. The mission has been designed to follow the conventional injection sequence; i.e., parking orbit,

870-14, Rev. AF

transfer orbit, and near-synchronous orbit. Attitude maneuvers will be performed to orient the spacecraft to the correct attitude prior to the Apogee Kick Motor (AKM) firing, which will occur at the 2nd (nominal), or the 4th (contingency) apogee. After AKM firing, drift phase orbital and attitude maneuvers will be performed to place the spacecraft at its final geostationary position.

C. COVERAGE

1. Coverage Goals

The coverage will consist of the 26-m antennas as prime and the 34- m antenna at Madrid as backup support for launch through drift orbit. Maximum support will consist of two 8-hour tracks per station for a 7-day period, plus 23 days of contingency support from all complexes.

2. Network Support

Svstem Goldstone 12 14 15 16

Canberra 42 43 45 46

Madrid 61 63 66

S-band TLM P P B P

S-band CMD

S-band TRK

NOTE: P = Prime B = Backup

Svstem nk (MHz)

S-band TLM N/A

S-band CMD

S-band TRK

Down;link (MHd Polarization

Vertical Linear Parallel

870-14, Rev. AF

Te 1 eme t r y

Data Streams Format Suwarrier Frequency Bit Rates Coding Record

Command

Format Subcarrier Frequency

Executive Tone Clock/Data Phase Bit Rate

Support

Uplink Power Antenna Rate Antenna Angle Rate Antenna Autotrack Doppler Rates Range Format

1 PCM (SP-L) /PSK/PM and FM/PM 48.25 kHz, IRIG 12, IRIG B 250 b/s N/A Required

PCM/FSK-AM/PM 8.6 kHz Sinewave for (1) tone 7.4 kHz Sinewave for ( 0 ) tone 5.79 kHz Sinewave 90 deg 128 b/s

1 to 10 kW Moderate Required Required (26-m only) Modest Tone (Prime) (100 kHz Major Tone) DSN Standard (Backup)

N/A Required

I . . . I Phase port ResponsWitv

Launch TaSC

Transfer/Drift Orbits DSN

Geostationary Orbit TACC (NASDA)

Contingency DSN (on request)

870-14, Rev. AF

ARY OPERATIONAL ENTAL SATELLITE (G METSAT PROJECT

Project Mgr: C. Thienel (GSFC)

LV/Range: Atlas Centaur/ETR MOM: K. Blaney (GSFC)

uunch Date : October 1992 - (I); May 1993 - (J); July 1995 - (K); February 1997 - (L); 2000 - (M)

Projected SC L ife/DSN SuDport : 5 years/Launch + 30 to 45 days

nsibilitv: Goddard Space Flight Center (GSFC) I . .

Source: SIRD December 1983 Sponsor: O S 0

The primary objective of the METSAT project is to provide a satellite system that meets the National Environmental Satellite Data and Information Service (NESDIS) requirements as specified by the National Oceanic and Atmo- spheric Administration (NOAA). For the GOES I-M spacecraft, these requirements include an Imager and Sounder system, a Space Environment Monitoring (SEM) System, a Data Collection System, and a Search and Rescue (SARI System. The SEM subsystems include a Solar X-Ray Sensor (XRS), an Energetic Particle Sensor (EPS), a High-Energy Proton and Alpha Detector (HEPAD), a Magnetometer, and an X-Ray Imager (XRI). The GOES I-M spacecraft will be designed to meet specified performance requirements for a period of 5 years.

870-14, Rev. AF

The GOES I-M mission profiles are identical. The NASA phase extends from liftoff through completion of spacecraft checkout (approximately 30-45 days after launch). The GOES I-M spacecraft are launched using an Expendable Launch Vehicle (ELV) from Kennedy Space Center (KSC). At completion of spacecraft checkout, operations are transferred to NOAA, which will operate the spacecraft for the remainder of the mission.

B. FLIGHT PROFILE

The GOES I-M spacecraft has been designed to be launched using an ELV. Additionally, the spacecraft has been designed to be retrieved by the Shuttle in the event of a Perigee Kick Motor (PKM) or similar failure that would prevent the spacecraft from leaving low Earth orbit.

1. STS Launch and GOES I-M Development Philosophy

The GOES-I/M spacecraft will be launched, maneuvered into geostationary orbit, and checked out in orbit by the NASA/GSFC flight operations team using NASA, Air Force, and NOAA ground systems. The NASA phase of the GOES-I/M mission will be designed to satisfy the following mission objectives:

(a) Ensure the health and safety of the spacecraft from launch through handover to NESDIS.

(b) Conduct on orbit testing of the satellite and instruments to characterize system performance.

(c) Hand over the spacecraft to NOAA for operations with sufficient on-board propellant for a minimum of five years of stationkeeping.

2. Satellite Transfer Orbit Philosophy

The GOES-I/M spacecraft will be launched from KSC using Atlas G/Centaur D-1A expendable launch vehicles.

Approximately four minutes before liftoff, the satellite is switched to internal battery power. During the launch vehicle ascent phase, spacecraft telemetry is relayed to MSOCC using the STDN stations at MILA and Bermuda. After Atlas/Centaur separation, the Centaur upper stage performs two main engine burns to place the satellite into an elliptical orbit with the apogee close to geosynchronous altitude. Prior to satelite separation, the Centaur upper stage performs a reorb maneuver to ensure that the GOES omni antenna rotation is normal to the plane of the earth to eliminate look-angle nulls.

The DSN stations (Canberra, Goldstone, and Madrid) are used for Telemetry, Tracking, and Command (TT&C) operations. The DSN is supplemented by telemetry and commanding capability from the NOAA Wallops CDA station. Each DSN station complex is fully redundant within itself.

870-14, Rev. A F

C. COVERAGE I

1. Coverage Goals

The coverage r equ i r ed f o r launch and t h e suppor t of t r a n s f e r and d r i f t o r b i t s w i l l c o n s i s t of t h e 26-m antenna a s p r i m e and t h e TBD antenna as backup f o r 11 days a t a l l complexes. The re w i l l a l s o be contingency suppor t f o r 15 days, f o r on - s t a t ion s p a c e c r a f t checkout. A f t e r t h e i n i t i a l 30-45 days, t h e DSN is committed f o r emergency suppor t . Contingency and emergency suppor t w i l l be provided by Goldstone only .

2 . Network Support

T h e suppor t provided by t h e D S N i s i n d i c a t e d i n t h e fo l lowing tab le :

Svstem Goldstone Canberra

12 14 15 16 17 42 43 45 46 61 63 66

S-band TLM P B B P B P

S-band CMD P B B P B P

S-band TRK P B B P B P

NOTE: B = Backup; P = P r i m e

A f t e r checkout, a l l normal CMD and TLM suppor t i s t o be provided by NOAA (Command and D a t a Acqu i s i t i on ) f a c i l i t i e s a t Wallops I s l and , V a . NASA cont ingency suppor t fo l lowing handover w i l l be committed on a non in te r f e rence basis w i t h ongoing NASA miss ions .

Frequencies a r e a l l o c a t e d accord ing t o t h e fo l lowing table:

S-band TLM -- 2209.086/2208.586 RCP

S-band CMD 2034.2

S-band TRK 2034.2

2209.086

870-14, Rev. AF

The support parameters f o r the Telemetry, Command, and Support Systems are listed below:

Telemetry

Data Streams Format

Bit Rate Record

Command

Support

Uplink Power Antenna Rate

Antenna Angle Data Antenna Autotrack Doppler Rates

Range Format Reco rdi ng . Digital

1 PM 1024 MHz subcarrier Manchester I1 2 kb/s Required

PCM/PSK/PM 1 kb/s 16 KHz

10 kW Nil, except for launch and transfer orbit Not required Launch and transfer orbit Nil, except for launch and transfer orbit Tone (Prime) DSN standard (Backup)

Required

I . a , . Phase port Respoxxubilitv

STS Shuttle Launch ELV Launch Transfer/Drift Orbits Geostationary Orbit Emergency Support

JSC STDN/KSC

NOAA/CDA DSN

870-14, Rev. AF

(Reimbursable)

Project Mgr: H. Schmeller (GSOC) MOM: G. Hiendlmeier (GSOC)

Launch Date: Launched June 5, 1989; Launched July 24, 1990; July 1992 Projected SC Life/DSN SUDDOKt : 10.1 years/30 days

D project ResDonsibility: Research Agency for Aerospace Technology,

Germany (DLR)

Source: SIRD December 1985/1989 Sponsor: DLR

The German Telecommunications Satellite (DFS) program is to provide telecommunications service for high data rate transmission of text and video data to the Federal Republic of Germany within the 11 GHz to 14 GHz and 20 GHz to 30 GHz bands. The space segment of this program is composed of three satellites, DFS-1, DFS-2, and DFS-3, which will be located at 23.5OE longitude of the geostationary orbit.

B. FLIGHT PROFILE

The DFS will be launched from the Centre Spatial Guyanis in French Guiana on an Ariane launch vehicle. The mission follows the typical injection

870-14, Rev. AF

sequence; i.e., parking orbit, transfer orbit, and drift orbit. Attitude maneuvers will be performed to orient the spacecraft prior to Apogee Kick Motor (AKM) firing. After AKM firing, drift phase orbital and attitude maneuvers will be performed to place the spacecraft in its final geostationary position.

C. COVERAGE

The DSN will support the transfer and drift orbit mission phases. The USAF 10s station will provide early support to DFS pre-Canberra AOS.

1. Coverage Goals

The coverage will consist of the 26-m initial acquisition at Canberra followed by 34-m support at Goldstone and Canberra as prime support for the transfer and drift orbits. Maximum support will consist of two 8-hour tracks per station for a 9-day period, plus 14 days of contingency support.

2. Network Support

Svstem Goldstone Ganberra Madrid

12 14 15 16 42 43 45 46 61 63 66 -

S-band TLM P P * 0

S-band CMD

S-band TRK

- P * 0

P * 0 -

NOTE: = Prime 0 = option *26m S-band support for initial acquisition

CTA 21 and GSFC test van will support compatibility testing with the DFS S/C TT&C "suit-case" model at approximately launch minus 7 months. These tests will verify and test the spacecraft RF compatibility with the DSN.

870-14, Rev. AF

Svstem Uplink (MHz) Downlink (MHz)

S-band TRK 2027.752 2201.600 RCP

(1 ) Telemetry

Data Streams 1 Format PCM(SP-L) /PSK/PM Subcarrier Frequency 32768 Hz Bit Rate 512 b/s Record Required

( 2 ) Command

Format PCM (NRZ-L) /PSK/PM Bit Rate 500 b/s Subcarrier Frequency 8000 Hz

( 3 ) Support

1 to 1 0 kW Moderate Required Required (26-m antenna, only) Modest Tone (100 kHz major tone)

Required Required

Phase . a . ort R e m i l i t v

Ariane Launch Transfer/Drift Orbits Geostationary Orbit

CSG DSN DFVLR

870-14, Rev. AF

. 870-14, Rev. AF

EXTENDED MISSION

(Cooperative)

TDS Mgr: D. Enari NOPE: R. Rose

Project Mgr: M. Grensemann (ESTEC) MOM: D. E. B. Wilkins (ESOC)

Launch Date: July 15, 1985

Projected SC Life/DSN Support:

. I , -ct Resoonsibility : European Space Agency (ESA)

Source: SIRD December 1990 Sponsor: ESA Program Manager: G. Strobe1

The primary objectives of the Giotto Extended Mission (GEM), are to determine the composition and physical state of the Grigg Skjellerup comet's nucleus; to determine the processes that govern the composition and distribution of neutral and ionized species in the cometary atmosphere. I

Prior objectives of Giotto were the same as those for Halley's comet in March, 1986.

870-14, Rev. AF

B. FLIGHT PROFILE

Giotto consists of a single European Space Agency (ESA) spacecraft that was launched in 1985 from Centre Spatial Guyanis in French Guiana on an Ariane launch vehicle. After a successful launch into geostationary orbit and a heliocentric transfer trajectory, the spacecraft successfully encountered Halley's comet in 1986.

One month after encountering Halley's comet, March 1986, the spacecraft was placed in hibernation in a heliocentric orbit slightly less than 1 A.U. Between February 1990 and July 1990 the spacecraft was successfully reactivated, checked out, placed on a trajectory course to intercept comet Grigg Skjellerup in July 1992. The spacecraft has been in hibernation since July 1990.

C. COVERAGE

1. Coverage Goals

The telecommunication link threshold is influenced by the distance of the spacecraft from the Sun and the aspect angle of the spacecraft with respect to the Sun and Earth. Additional coverage is being provided by the DLR Weilheim, Germany, and ESA Perth, Australia, tracking stations. Stage I and Stage I1 of the Giotto Extended Mission have been completed. The DSN is committed to supporting the Stage I11 SIRD, whose requirements are listed below.

The DSN expects to meet these coverage goals even though requirements are in excess for the 70-m and 34-m standard subnets. View periods and other user requirements are not in direct conflict with Giotto during the Stage I11 support.

on Phase Period I .

Stage I

Reactivation Phase 2/90 - 3/90

Scientific Payload 4/90 Check Out Phase

Near Earth Phase 5/90

Stage I1

Earth Flyby and 7/90 Hibernation 1x1

(30 days) PassesLPlonth

Antennas

34 STD

870-14, Rev. AF

(30 days) Period -Antennas

Stage I11

Reactivation Phase 5/92 21 70-m

Cruise Operations 6/92 16

Rehearsals and 6/92 - 7/92 12 Encounter

70-m/34 STD

2. Network Support

12 14 15 16 42 43 45 46 61 63 65 66

S-band TLM P P

X-band TLM P P

S-band CMD P P

S-band TRK P P

X-band TRK P P P P P P

FREQUENCY ASSIGNMENTS

Svstem YPlink mHz1 tion

S-band TLM -- 2298.703704 RCP

X-band TLM -- 8428.580248 RCP

S-band CMD 2116.72 - RCP

S-band TRK 2116.72 - RCP

X-band TRK -- 8428.580248 RCP

870-14, Rev. AF

The support parameters for the are listed below:

(1 ) Telemetry

Data Streams Format Subcarrier Frequency

Record

(2) Command

Format Bit Rate Subcarrier Frequency Subcarrier Waveform

(3 ) Support

Uplink Power

Antenna Rate Antenna Angle Data Doppler Rate Range Format Recording . Analog . Digital

Telemetry, Command, and Support Systems

1 (S- or X-band) PCM/PSK (uncoded/coded) 46.080 kHz for 360 b/s 276.480 kHz for 5760, 23040 and 46080 b/s DODR Required

PCM/PSK 125/8 b/s (15.625 b/s) 16 kHz Sine

up to 20 kW (34-m), 100 kW (70-m) Sidereal Not Required Moderate to High Standard DSN

Not Required Required

. . * * . ission Phase Dor t ResDonsibility

Stage I Stage I1 Stage I11

DSN/ESA-Perth/DLR-Weilheim D SN/ E SA DSN/ESA-Perth/DLR-Weilheim

870-14, Rev. AF

LAR SYSTEM R

TDS Mgr: H. Cox NOPE: P. Wolken

Science Mgr: N. A. Renzetti MOM: TBD

ODerational Date: April 1, 1985 Projected DSN SupDort: Continuous

Proiect Responsibilitv: Jet Propulsion Laboratory (JPL)

Source: SIRD January 31, 1989 Sponsor: O S 0 Program Manager: S. Ostro

The primary objective of the Goldstone Solar System Radar is the investigation of solar system bodies by means of Earth-based radar. of primary interest include the Galilean moons, Saturn’s rings and moons, and Earth-approaching asteroids and comets. Planets are also of interest, particularly Mercury and the planets to which NASA has not yet planned spacecraft visits.

Targets

B. PROGRAM PROFILE

Based on a history of solid achievement, includng the definition of the Astronomical Unit, imaging and topography of Mars, Venus, and Mercury, and contributions to the general theory of relativity, the program will continue

870-14, Rev. AF

to support Flight Project requirements and its primary objectives. The individual target objectives are as follows:

Galilean Moons: X-band observations will be used to put some limits on the small-scale structure of the regolith.

Mercury : Construct radar maps of portions of the unimaged hemisphere at -10-km resolution. Make a series of closure-point ranging measurements to be used for testing gravitation theories, including general relativity. Some of this work is coordinated with Arecibo observations, as part of a cooperative effort to minimize systematic sources of error. Refine estimates of Mercury's pole direction, to evaluate available theoretical explanations for the planet's spin/orbit resonance.

Venus :

Moon :

Mars :

Refine the rotation period and pole direction as much as possible prior to Magellan's orbital insertion. Obtain high-resolution (to -1 km) radar images of surface regions that cannot be mapped from Arecibo, at very small incidence angles (8 near 0"), i.e., with a viewing geometry very different from that (8-30") in Magellan images. Locate geologically interesting regions as candidates for Magellan high-resolution investigation. Refine existing estimates of Fresnel reflection coefficients for surface units with anomalously high radar albedoes, and determine those regions' angular backscattering law.

Construct 100-to-200-meter-resolution images of selected regions in each component of the Stokes vector, to elucidate the scattering mechanism and the nature of near-surface structure, and to constrain the electrical properties of the regolith. Measure topography in selected areas, to refine geologic interpretations of lunar landforms.

Maintain the accuracy of the Mars orbital ephemeris. Measure surface topography at tropical latitudes (k20"). Determine the surface reflectivity and effective slope for multiple ground tracks within the tropics. Use dual-polarization, cw measurements and joint Goldstone-VLA bistatic observations to elucidate the global variations in the surface's small-scale structural complexity. Constrain the surface's gross geometry at scales (-1 cm to -10 m) relevant to the safe landing and maneuverability of a spacecraft. Test hypotheses about temporal variations in radar reflectivity that might result from seasonal melting of subsurface ice.

870-14, Rev. AF

Phobos and Deimos :

Near-Earth Asteroids:

Ma inbe 1 t Asteroids:

Comets :

Detect 3.5-Cm radar echoes and estimate each satellite's radar albedo, polarization signature, and angular scattering law. Constrain the satellites' surface bulk density and small-scale roughness.

Secure recovery of newly discovered objects. Refine orbits of previously observed objects. Use delay/ Doppler imaging to obtain information about dimensions, shapes, and spin vector. Constrain surface's dual-polarization scattering properties and elucidate near-surface characteristics at cm-to-km structural scales. Measure the asteroid's radar cross section; estimate the radar albedo and use it to bound the regolith bulk density, porosity, and metal concentration.

Using time-delay measurements, shrink the line-of- sight component of positional error ellipsoid. Use power spectra to constrain pole direction and diameter. Estimate surface slope at topographic scales, and near-surface roughness at small scales. Measure the asteroid's radar cross section; estimate the radar albedo and use it to bound the regolith bulk density, porosity, and metal concentration.

Search for clouds of large (2 cm) particles near the nucleus, such as those discovered around Halley and IRAS-Araki-Alcock. Image the nucleus and determine its size, shape, spin properties, and surface characteristics. Refine estimates of orbital elements, to clarify the dynamical history of long- period comets and to assist spacecraft navigation during missions to short-period comets.

Europa, Ganymede, ' and Callisto: Determine the 3.5-cm radar albedo and circular

polarization ratio of each of these icy satellites, whose 13-cm properties are extraordinary. Use the results to constrain existing theoretical explanations for the bizarre radar signatures. Search for radar features, localize them, and seek correlations with features in Voyager (and eventually Galileo) images. Refine the prediction ephemerides for each satellite, especially Callisto, to assist targeting of the Galileo spacecraft, by measuring echo Doppler frequencies. depends on echo strength, and radar measurements with the minimum precision required for ephemeris improvement cannot be obtained during 1993-98 unless Goldstone has a 1.0-megawatt transmitter.

The precision of Doppler estimates

870-14, Rev. AF

Io : Obtain the first 3.5-cm radar detection of this volcanically active satellite, and use estimates of radar properties to provide information about the surface bulk density and small-scale roughness.

Saturn's Rings: Use delay-Doppler images in each Stokes vector component to constrain the manner in which radar waves are backscattered from the classical ring sections, and to infer the physical properties of ring particles. Use bistatic observations, with Goldstone transmitting and the VLA receiving, to image the ring system at 1200-km resolution.

Saturn's Icy Satellites:

Titan:

Detect the first radar echoes from Iapetus and possibly Rhea, to ascertain whether these objects, whose surfaces contain nonwater ices, share the unusual radar properties of Jupiter's icy moons.

Detect the first radar echoes from Titan, and measure this object's radar albedo and angular scattering law. These measurements would constitute mankind's first direct measurements of Titan's surface. They would permit evaluation of the diverse models proposed for the configuration of Titan's surface, which might be at least partially covered by a deep, ethane-rich ocean.

C. COVERAGE

1. Coverage Goals

For this program, the coverage goals vary significantly with the target of opportunity. All of these goals (listed Table 1) require the support of DSS 14, which is the only facility with the necessary high-power transmit capability, and occasional support from DSS 12 and DSS 13. DSS 18 will replace DSS 12 in mid-1993. A replacement 34-m antenna (also designated DSS 13) will replace the current DSS 13 in 1992 for X-band reception and at a later date for S-band reception.

Table 1 lists the estimated GSSR usage for 1990-2000.

870-14, Rev. AF

Table 1. Estimated Program Support for 1990-2000

Opportunities Tracks Per Targets Per year Opportunity Tracks Per year

Mars 1 per 2 to 6 years

Venus 1 per 1 to 6 years

Jupiter 1

Saturn 1

Objects 6

Asteroids 4 5 20

Mercury 3 7 21

Moon 1 5 1 15

Total Tracks per year 180

Average Tracks per Month 15

NOTE: One radar "track" consists of 8 hours of observing time, preceded by 1 . 5 hours of pre-cal and followed by 0.5 hours of post-cal. Each track requires DSS 1 4 . Interferometric observations (most Venus and selected Mercury tracks) also use DSS 13 and one other 34-m station.

The 10-year period covered by these estimates will include planetary encounters and prolonged planetary operations by several major flight projects. For this reason, it is considered unlikely that the DSN could sustain the average level of radar support requested while meeting its commitments to in-flight projects. It is estimated that 50 percent of the requested support is a more realistic expectation on which the program should base its science planning.

2. Network Support

Specific requirements for antenna time on DSS 1 4 are prepared on a yearly basis and submitted to the scheduling office for negotiation at least 6 months ahead of the earliest need date. The facility support to be provided by the DSN is indicated in the following table:

.Svstem

S-band RAD

X-band RAD

NOTE : P=Prime

870-14, Rev. AF

P Antenna support requirements for

P in the JEMS GSSR bulletin board 6 months ahead are published

which is updated on a weekly basis.

3. Compatibility Tests

Compatibility testing with DSN systems will be supported by the DSN Radio Astronomy Unit. This data type is not required to be supported by the DSN ground data system.

Svstem nk [MHz) Downlink (MHz) Polarization

S-band

X-band

2320.00

8495.00

2320.00

8495.00

The support parameters for the Telemetry, Command and Support Systems are listed below:

Telemetry

No support required

Command

No support required

Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Format Recording . Analog . Digital . VLBI

400 kW Side rea 1 Requ i red Requf red Moderate None

Not Required Not Required Not Required

870-14, Rev. AF

. . I - Dart Respons-

Implementation

Planetary Operations

DSN (331)

DSN (440)

870-14, Rev. AF

(This page intentionally lef t blank.)

870-14, Rev. AF

B ? i kf

HIPPARCOS

Launch Date: Launched August 8, 1989

Project Resw -onsibilitv: European Space Agency (ESA)

Source: SIRD Sponsor: NASA/ESA

The primary objective of Hipparcos is to provide very accurate star map data and star position accuracies on the order of 2 arc seconds.

B. FLIGHT PROFILE

Hipparcos was planned to be in a geostationary orbit, but due to failure of the apogee motor, it is currently in a high elliptical orbit and has a 10.8 hour period.

C. COVERAGE

Goldstone 26-m will provide 6-8 hours per day support for real-time telemetry and command. Mission-dependent equipment is required at Goldstone, and telemetry and command data will be transmitted from Goldstone to European Space Operations Control Center (ESOC) via satellite links. Operations support is scheduled to begin March 12, 1990.

870-14, Rev. AF

HUBBLE SPACE TELESCOPE (HST)

(Emergency Support)

NSM: N. A. Fanelli NOPE: R. E. Nevarez

Project Mgr: F. Wojtalik (MSFC) MOM: J. Repass (GSFC)

LV/Range: STS/ETR

Launch Date: Arpil 24, 1990 ?roiected SC L ife/DSN Support : 15 years

Froiect ResDonsibilitv: Marshall Space Flight Center/ Goddard Space Flight Center

Source: NSP March 1983 Sponsor: OS0

The Space Telescope is a national facility. It consists of a 2.4-m aperture Ritchey-Chretien cassegrain telescope weighing approximately 9525 kg with various energy detectors designed for the observation of IR, visible, and W wavelengths (0.12 to 1000 microns).

B. FLIGHT PROFILE

The space telescope was deployed into a 28.5-degree inclination, circular orbit, which permits a mission lifetime of 15 years. Orbit: Decaying circular between 594 and 400 km x 28.5 deg; period = 95 minutes.

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

The DSN is responsible for providing contingency support for the space telescope in the event a Tracking and Data Relay Satellite System (TDRSS) or spacecraft failure prevents communications via that link.

2. Network Support

1 2 1 4 1 5 1 6 42 43 45 46 6 1 63 66

S-band TLM E E E

S-band CMD

S-band TRK

NOTE: P = Prime E = Emergency support

Svstem Downlink (MHz) P o l a r i z a t i o n

S-band TLM -- 2287.5 LCP

LCP S-band CMD 2106.4063

S-band TRK 2106.4063 2287.5 LCP

870-14, Rev. A F

(1 ) Telemetry

Data Streams

Format Subca r r i e r Frequency B i t R a t e

Recording Analog

(2 ) Command

Format B i t Rate Subca r r i e r Frequency

( 3 ) Support

U p l i n k Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler R a t e s Range Format R e c o rd i ng . Analog . D i g i t a l

PCM/PM Big-L None Engineering: 5 0 0 b/s, 4 kb/s,

32 kb/s, 1 0 2 4 kb/s

Requ i red

PCM/PSK/PM 1 kb/s 1 6 kHz

TBD Mode r a t e Required Requ i red TBD TBD

R e q u i r e d Not r e q u i r e d

The a l l o c a t i o n of r e s p o n s i b i l i t i e s f o r t r a c k i n g suppor t i s l is ted i n t h e fo l lowing t a b l e :

I , I . . i o n Phase port R e s p o n s b i l l t y

STS Launch E a r t h O r b i t Contingency Support

TDRS S TDRS S DSN

870-14, Rev. AF

INTERNATIONAL COMETARY EXPLORER

Project Mgr: P. Pashby (GSFC) MOM: R. Wales (GSFC)

Launch Date: Aug. 12, 1978 Projected SC JA.#k/DSN Sumort: 34 years/l5 years

Project Rwonsibilitv: Goddard Space Flight Center (GSFC)

Source: SIRD N vember 1985

=--. ~ ---_

, "5ponsor: oso 4,/ ./

The primary mission objectives of the International Cometary Explorer (ICE) comet mission are to determine the composition and physical state of the Giacobini-Zinner comet's nucleus; to determine the processes that govern the composition and distribution of neutral and ionized species in the cometary atmosphere; and to investigate the interaction between the solar wind and the cometary atmosphere.

B. FLIGHT PROFILE

The spacecraft was in a halo orbit around the Sun-Earth libration point until it was moved June 10, 1982 to the Earth's Geomagnetic Tail (GT). The spacecraft reached the GT in January 1983 and remained there until December 1983, at which time a lunar swing-by placed the spacecraft in a trajectory heliocentric orbit which encountered the comet Giacobini-Zinner in September

870-14, Rev. AF

1985. The spacecraft provideed observations of the solar wind up-stream o f

C. COVERAGE

1. Coverage Goals

Coverage by the 64-/70-m ante

comet Halley in 1986.

nas has been provid d from January 1984 to date and will continue through the end of mission, consisting of cruise and encounter support. (Prime support will be provided by the Madrid and Goldstone complexes, with additional support from the Canberra complex.)

The 64-m station at Usuda Japan, which is part of the Japanese Institute of Space and Astronautical Science (ISAS), provided supplemental support from May 1985 through Giacobini-Zinner encounter (September 1985), and during the first Halley Radial (October 1985). Support consists of making telemetry recordings, which will be processed in nonreal-time at JPL. The number of hours of coverage (per day/week) will be determined by negotiation between NASA and ISAS.

Limited extended mission coverage will be provided from May 1986 through end of mission.

2. Network Support

Svstem Goldstone

12 14 15 16

S-band TLM P

S-band CMD P

S-band TRK B P

NOTE: P = Prime B = Backup S = Supplemental

Canberra Madrid Usuda

42 43 45 46 61 63 66

870-14, Rev. AF

Frequencies are a l l o c a t e d according t o t h e fo l lowing table:

Svstem Uplink (MHz) Downlink (MHz 1 P o l a r i z a t i o n

S-band TLM

S-band CMD

S-band TRK

2090.66

2041.95

2090.66

The suppor t parameters f o r t h e a r e l i s ted below:

Telemetry

Data Streams Format Coding Subca r r i e r Frequency B i t Ra tes

R e c o r d i ng

Command

Forinat S u b c a r r i e r Frequency B i t R a t e

Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rate Range Format Recording

. Analog

. D i g i t a l

2270.4

2217.5

2270.4

Telemetry, Command, and Support Systems

1 PCM(SP-L) /PM o r PCM(NRZ-L) /PSK/PM Convolut ional , K = 24 R = 1 / 2 1024 H Z (16-256 b / s ) 16 , 32, 64, 128, 256, 512, 1024, and 2048 b/s Required

PCM/FSK-AM/PM Fo: 9000 Hz, F1: 7500 H z 256 b/s

1 0 t o 80 k W S i de re a1 Not r equ i r ed Not r equ i r ed S ide rea 1 DSN Standard

Not r equ i r ed Required

8 IO -1 4, Rev. AF

I . ission Phase

Earth Orbit Planet a ry

. . . ort R e s p o n s w

STDN (through Dec. 1983) DSN (after Dec. 1983)

870-14, Rev. AF

INTERNATIONAL SOLAR TERRESTRIAL PHYSICS (ISTP) p -2 it PROGRAM #$9 i ,#

TDS Mgr: J. P. Goodwin Project Mgr: K. 0 . Sizemore NOPE: S. Wolf MOM: D. Muhonen (GSFC) (SOHO and CLUSTER)

MOM: R. Sanford (GSFC) (GEOTAIL, WIND, POLAR)

* . 1ss1on

GEOTAI L

CLUSTER ( 4 )

Acrencv - LLY Range

(ISAS) July 1992 NASA Medium ELV ETR

(NASA) December 1992 NASA Medium ELV ETR

(NASA) July 1993 NASA Medium ELV WTR

(ESA) March 1995 NASA Intermediate ELV ETR

(ESA) December 1995 Ariane

/--- -\ CSG

Source: GEOTAIL - SIRD March 1990 WIND and POLAR - SIRD Draft 2, May 1990

SOHO - Preliminary SIRD, Issue 2, August 1989

CLUSTER - Preliminary SIRD, August 1987

--__. ~

870-14, Rev. AF

A. PROGRAM DESCRIPTION

The International Solar Terrestrial Physics (ISTP) Program is a large, multi-national program involving three space agencies and up to eight spacecraft. NASA, together with the Institute of Space and Astronautical Science (ISAS) and the European Space Agency (ESA), has agreed in principle to coordinate their efforts in investigating the Sun and the Earth. Each agency is planning to construct and operate different spacecraft as part of this cooperative venture: Geotail provided by ISAS, Solar Heliospheric Observatory (Soho) and Cluster (four spacecraft) contributed by ESA, and Wind and Polar by NASA.

B. GENERAL DESCRIPTION

NASA contributions to the various ISTP missions are specified in two major initiatives:

(1) Collaborative Solar Terrestrial Research (COSTR) Initiative

( 2 ) Global Geospace Science (GGS) Initiative

The COSTR Initiative will combine resources and scientific communities on an international scale to undertake the development of instruments and their appropriate support elements, along with ground-based theory investigations in the context of a comprehensive program of solar-terrestrial physics. This program will study the overall balance and nature of solar- terrestrial interaction of the GEOSPACE region. These joint NASA-ESA-ISAS missions will carry instruments operated by an international team of principal investigators. The missions will be launched by various launchers and supported by the international ground-based networks and systems.

Specifically, COSTR defines the NASA contribution in terms of instruments, launch vehicle, and launch tracking and operations support for the Geotail, Soho, and Cluster missions.

The objective of the GGS Initiative is to undertake the development of two spacecraft and their appropriate support elements, and ground-based and theoretical investigations in the context of a comprehensive program of solar- terrestrial physics. This program in solar-terrestrial physics research will measure, model, and quantitatively assess the processes in the Sun-Earth interaction chain by the use of simultaneous spacecraft placed in complementary orbits.

Specifically, GGS defines the complete requirements which will be filled by the Wind and Polar missions.

The ESA contributions to the ISTP are defined in the ESA Solar Terrestrial Science Programme (STSP) .

870-14, Rev. AF

INTERNATI NAL SOLAR TE RESTRIAL PHYSICS

TDS Mgr: J. P. Goodwin NOPE: S. Wolf

Project Mgr: K. 0. Sizemore (GSFC) MOM: R. Sanford (GSFC)

L/V Range: Delta I1 7925/ETR

Launch Date : July 1992 Proiected SC Life/DSN Support : 24 months Prime (1-year ext.) /3 years

sDons&ulitv: JPL Lead Network (ISAS Cooperative) . I .

Source: SIRD (GSFC) Sponsor: ISAS-OS0

A. GENERAL

The Geotail spacecraft will be provided by ISAS and will be a spin- stabilized cylindrical spacecraft 2.2 m in diameter and 2.3 m in height with a despun antenna. NASA will provide a Delta Launch Vehicle, tracking support by the Deep Space Network (DSN), and data processing support by the Goddard Space Flight Center (GSFC). In exchange, ISAS will reserve part of the payload for NASA instruments together with a certain number of investigators from the United States.

As the solar wind flows toward the Earth, some of the energy is modified by the Earth's magnetosphere, ionosphere, and upper atmosphere. This interaction causes the flow to be altered, creating a plasmasphere, plasma sheet, and ring currents in the Earth's Geomagnetic tail region. The result is a series of distinct regions which affect processes on the Earth. By traversing the tail region to a variety of depths, Geotail will be able to determine the

870-14, Rev. AF

size, position, and other properties of these regions. When correlated with information obtained from the other ISTP spacecraft, Geotail data should help to provide a more complete understanding of how the solar processes affect the Earth's environment.

B. FLIGHT PROFILE

The first launch of the COSTR Initiative will be the ISAS spacecraft Geotail. Presently, Geotail's launch will be in July 1992. The primary mission will have a duration of 24 months and an extended mission phase, lasting 1 year, can be expected. Two orbital phases are planned for Geotail.

In Phase 1, the Moon's gravity is used to control apogee, perigee, and orbital position in the magnetosphere by means of double lunar swingbys. Apogees will range from approximately 80 to 250 Re while perigees will vary between 5 and 10 Re. The orbital period during this phase will be 1-, 2-, and 3-month orbits, starting with the first lunar swingby in September 1992.

In Phase 2 Geotail will be moved to a lower geocentric orbit having dimensions of 8 x 30 Re. The orbital period during this phase will be approximately 4.9 days, starting in May 1994.

Orbits in both Phase 1 and Phase 2 will lie in or near the Moon's orbit plane.

C. COVERAGE

Primary ground station support will be from the USUDA 64-m station for 8 hours/day, 5 days/week. (S - and X-band).

DSN support will consist of receiving between three and four tape recorder data transfers per day, over two or three DSN stations. Each transfer of data takes 2 hours at 65 kb/s or 1 hour at 131 kb/s (S-band only). The bit rate will depend on the spacecraft range and whether support is from a 26- or 34-m station.

The 26-m stations are baselined for Geotail support. However, portions of the mission will be supported by the 34-m STD stations.

12,14,15,16 61,63,66

S-band TLM

S-band TRK

B P B P B P

870-14, Rev. AF

S-band 2081.0 2259.91

X-band -

(1 Telemetry

Real time contingency 65.5 kb/s or 16.4 kb/s or

Playback 131 kb/s or 65.5 kb/s

(2) Command

(3) Ranging (Not simultaneously with Telemetry)

8474.66 (contingency Telemetry support by DSN)

PCM(NR2-S) Conv, BiOL, PM

PCM(NRZ-S) Conv, BiOL, PM

Not Required

DSN Standard

Phase . I *

DO rt Re m o n s JJXLLLQ

Launch - L+2 weeks Approx. 2 passes/month (around maneuvers) Other than above

DSN DSN

The Geotail spacecraft will be operated from the Geotail POCC at ISAS. CMD will be via Usuda.

870-14, Rev. AF

TDS M g r : J. P . Goodwin NOPE: S. Wolf

P r o j e c t M g r : K . 0. Sizemore (GSFC) MOM: R. Sanford (GSFC)

L/V Range: D e l t a I1 7925/ETR

J-e: D e c e m b e r 1992 P r o j e c t e d SC Jpife/DSN Support: 24 months P r i m e (1-year e x t . ) / 3 y e a r s

P r o i e c t Respons ib i l i t v : GSFC I , ,

Source: SIRD (GSFC) May 1990, Dra f t 2 Sponsor: ISAS-OS0

The launch of t h e WIND s p a c e c r a f t w i l l p l a c e t h e s a t e l l i t e i n t o a sun- side apogee double- lunar swing-by o r b i t f o r a p e r i o d of one year , a f t e r which W I N D may be t r a n s f e r r e d t o a Sun-Earth L1 Halo o r b i t .

B. COVERAGE

The W I N D s p a c e c r a f t w i l l c a r r y a NASA s t anda rd u s e r s t ransponder and w i l l normally communicate wi th t h e WIND ground f a c i l i t i e s v i a a s p a c e c r a f t Medium Gain Antenna (MGA) and t h e DSN S-band s e r v i c e . One 2.08-hour suppor t i n t e r v a l each day w i l l be r equ i r ed f o r r ece iv ing t a p e r eco rde r playback data. Real-time t e l eme t ry f o r s p a c e c r a f t and instrument-performance monitor ing w i l l be r ece ived on a s u b c a r r i e r s imultaneous with t h e t a p e r eco rde r playback. Spacec ra f t commanding i s r equ i r ed throughout t h i s p e r i o d wi th (TBD) minutes of ranging and range- ra te suppor t . The s p a c e c r a f t r e q u i r e s t h a t command suppor t pe r iods be no more t h a n 36 hours a p a r t du r ing t h e prime mission.

24-1 WL

870-14, Rev. AF

The 26-meter DSN stations at Canberra, Goldstone, and Madrid are designated prime support stations, with the 34-meter standard subnet located at these facilities used for backup support, or when insufficient link margins exist in the mission orbit to acquire usable data.

Svstem Goldstone - Madrid

12,14,15,16 42,43,45,46 61,63,65,66 S-band TLM B P B P B P

S-band CMD B P B P B P

S-band TRK B P B P B P

C. FREQUENCY ASSIGNMENTS AND DATA RATES

Svstem

S-Band CMD S-Band TLM S-Band TRK

D. SUPPORT PARAMETERS

UDlink

2094.896 MHz

2094.896 MHz ---

(1 ) Telemetry Real time 5.565 kb/s

11.3 kb/s

Subcarrier Playback 64 kb/s or

32 kb/s

128 kb/s

(2) Command Format Bit rate Subcarrier Frequency Subcar rie r Waveform

Down1 ink

--- 2275.000 MHz 2275.000 MHz

pCM(NRZ-L), Conv, R-S, BigL, PSK, PM

2 x RT at < 60 Re

1.28 MHz sine wave pCM(NRZ-L), Conv, R-S, BiBL, PM

at < 60 Re

PCM/PSK/PM 250 b/s 16 kHz Sine

(3) Ranging DSN Standard

870-14, Rev. A F

TDS Mgr: J. P. Goodwin NOPE: S. Wolf

P r o j e c t M g r : K . 0. Sizemore (GSFC) MOM: R. Sanford (GSFC)

L/V Range: De l t a I1 7925/WTR

J-f: J u l y 1993 P r o i e c t e d SC L ife/DSN Suwwort; : 24 months P r i m e (1-year e x t . ) / 3 y e a r s

P r o j e c t Reswons ib i l i tv : GSFC . I .

Source: P r e l i m . SIRD (GSFC) August 1987, and D r a f t 1 SIRD, August 1989 Sponsor: NASA-OS0

A. M I S S I O N DESCRIPTION

The p o l a r s p a c e c r a f t w i l l be launched from WTR i n t o a 2 e a r t h radii by 9 e a r t h r a d i i POLAR o r b i t , wi th apogee near t h e North Pole .

B. COVERAGE

The DSN w i l l p rovide a l l ISTP/GGS support a s s p e c i f i e d below.

The POLAR s p a c e c r a f t w i l l c a r r y a NASA s t a n d a r d u s e r s t ransponder , and w i l l communicate i n S-band wi th t h e POLAR ground f a c i l i t i e s v i a a s p a c e c r a f t HGA and t h e DSN S-band s e r v i c e . Four suppor t i n t e r v a l s p e r day (approximately 45 minutes each i n d u r a t i o n ) w i l l be r equ i r ed f o r r e c e i v i n g t a p e r eco rde r playback da ta , and up t o 1 2 hours p e r day f o r t h e f i r s t m6nth and 3.6 hours p e r day t h e r e a f t e r w i l l be needed f o r r ece iv ing r ea l - t ime wide-band d a t a . Real-t ime t e l e m e t r y f o r s p a c e c r a f t and ins t rument performance monitor ing w i l l be r ece ived on a s u b c a r r i e r s imultaneous with t h e t a p e r eco rde r playback on t h e main c a r r i e r . Spacec ra f t commanding i s requ i r ed throughout t h i s p e r i o d wi th (TBD) of ranging and range- ra te suppor t .

870-14, Rev. AF

The 26-meter subnet stations located at the DSN locations in Canberra, Goldstone, and Madrid are designated prime support stations, with the 34-meter facilities used for backup support.

C . FREQUENCY ASSIGNMENTS

Svstem

S-Band CMD S-Band TLM S-Band TRK

UDlink

2085.688 MHz

2085.688 MHz ---

D o w n l i a k

2265.0 MHz 2265.0 MHz

D. SUPPORT PARAMETERS

(1 1 Telemetry Real time 55 I 65 kb/s PCM (NRZ-L) , Conv, R-S , PSK, PM

on a 1.23 MHz sinewave subcarrier

Subcarrier Playback 512 kb/s or

256 kb/s

(2) Command Format Bit rate Subcarrier Frequency Subcarrier Waveform

PCM(NRZ-L) , Conv, R-SI PM

PCM/PSK/PM 1000 b/s 16 kHz Sine

( 3 ) Ranging DSN Standard

870-14, Rev. AF

LANDSAT 4 AND 5

(E mer g e n cy)

TDS M g r : N . A. F a n e l l i NOPE: R. E . Nevarez

P r o j e c t M g r : L. Gonzales (GSFC) MOM: W . Webb (GSFC)

LV/Range :

Launch Da te : LANDSAT 4 , J u l y 16, 1982 - LANDSAT 5, March 1, 1984 Projected SC T,ife/DSN SupDort : 4 t h q u a r t e r 1989/4th q u a r t e r 1989

p r o iect ResDons i b i l i t v : Goddard Space F l i g h t Center (GSFC)

Source: SIRD/NSP Sponsor: O S 0

The pr imary purpose of LANDSAT i s t o s tudy Ea r th resources . Each s a t e l l i t e c o n t a i n s a Thematic Mapper (TM) and a M u l t i s p e c t r a l Scanner (MSS) imaging dev ice p l u s mission unique hardware.

B. FLIGHT PROFILE

LANDSAT 4 i s c u r r e n t l y i n a c i r c u l a r Sun-synchronous o r b i t wi th o r b i t a l parameters of 699 km x 7 0 1 km x 98 degrees i n c l i n a t i o n . The o r b i t a l p e r i o d i s 99 minutes . LANDSAT 5 w a s launched i n t o a n e a r l y i d e n t i c a l o r b i t wi th pa ram- eters of 7 0 5 km x 705 km x 98.2 degrees.

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

The DSN will support LANDSAT 4 or 5 during emergencies that would prevent satellite-to-Earth communications using the standard TDRSS-White Sands data link. The DSN 26-meter antenna subnetwork would support these emergency situations.

2. Network Support

Svstem

S-band TLM

S-band CMD

12 14 15 16 42 43 45 46 61 63 66

S-band TRK E

NOTE: E = Emergency

Svstem Uplink IMHz) Pownlink (MHzL Polarization

S-band TRK 2106.4 2287.5 RCP

8 7 0 - 1 4 , R e v . AF

T h e support parameters f o r t he T e l e m e t r y , Command, and Support Systems are l i s ted b e l o w :

(1 ) T e l e m e t r y

D a t a S t r e a m s F o r m a t Subcarrier Frequency B i t R a t e s

( 2 ) Command

F o r m a t Subcarrier Frequency B i t R a t e

U p l i n k Power A n t e n n a R a t e A n t e n n a A n g l e D a t a A n t e n n a A u t o t r a c k D o p p l e r R a t e s R a n g e F o r m a t R e co rding . A n a l o g . D i g i t a l

1 PCM/PSK 768 k H z R T / 5 9 7 k H z P B 1 kb/s R T / 2 4 k b / s P B

PCM/PSK/PM 1 6 k H z 2 . 0 k b / s

1 6 W ( N o m i n a l ) Mode r a t e R e q u i r e d R e q u i r e d Mode r a t e S I N E

R e q u i r e d N o t required

T h e a l l o c a t i o n of responsibi l i t ies f o r t r ack ing support i s l is ted i n t h e fol lowing table:

. . i s s i o n Phase

E a r t h O r b i t ( P h a s e 1) E a r t h O r b i t (Phase 2 )

2 6 - 3

870-14, Rev. AF

LASER GEODYNAMIC SATELLIT (LAGEOS 11)

TDS Mgr: M. Traxler NOPE: T. Howe

Project Mgr: G. Ousley (GSFC) MOM: C. Portelli, AS1

LV/Range: Shuttle/KSC

Launch Date : August 31, 1992 Projected SC L ife/DSN SUDD -art: Many years/Launch plus 4-10 days

Project ResDons ibilitv : GSFC (Italian Cooperative - CNR)

Source: SIRD Project Documentation Sponsor: OS0

The Laser Geodynamic Satellite I1 (LAGEOS 11) is nearly identical to the LAGEOS I satellite, which was launched by NASA in 1976 . However, LAGEOS I1 is completely passive, and is equipped with fused silian corner reflectors for ranging with ground-based lasers. The addition of LAGEOS I1 will provide the GSFC laser network with significantly increased satellite tracking opportunities, because LAGEOS I is at a 110-degree inclination and LAGEOS I1 will be at a 52-degree inclination.

870-14, Rev. AF

B. FLIGHT PROFILE

LAGEOS I1 w i l l be launched from t h e Kennedy Space Center (KSC) on t h e Space Transpor t a t ion system (STS) s h u t t l e . The e s t ima ted o r b i t p r o f i l e i s a s fo l lows :

S h u t t l e : C i r c u l a r o r b i t a t 296 km. I n c l i n a t i o n a t 28.5 degrees.

Trans fe r O r b i t : E l l i p t i c a l o r b i t of 300 km by 5900 km. I n c l i n a t i o n a t 41 degrees. ( I t a l i a n Research I n t e r i m Stage ( I R I S ) w i l l be i g n i t e d over Malindi o r t h e Indian Ocean S t a t i o n . )

F i n a l O r b i t : C i r c u l a r o r b i t a t 5900 km. I n c l i n a t i o n a t 52 degrees. ( A t f i r s t t r a n s f e r o r b i t apogee, a MAGE-1 s o l i d rocket motor w i l l c i r c u l a r i z e t h e o r b i t and change t h e i n c l i n a t i o n . )

C. COVERAGE

1. Coverage Goals

The coverage w i l l begin a t release from s h u t t l e and cont inue f o r approximately t h r e e days. The I R I S burn coverage s t a t i o n w i l l p rovide real- t i m e t e l e m e t r y on t h e I R I S burn, and Goldstone, Canberra, Hawaii and Guam S t a t i o n w i l l p rovide r ea l - t ime t e l eme t ry on t h e MAGE-1 burn. The DSN 26-m subnet w i l l p rovide t r a c k i n g d a t a on t h e LAGEOS Apogee Stage f o r a p e r i o d up t o 3 days .

2 . Network Support

The suppor t provided by t h e DSN i s i n d i c a t e d i n t h e fo l lowing t a b l e :

12 14 15 16 42 43 45 46 61 63 66

S-band TLM P P S

S-band TRK (1-way)

NOTE: P = P r i m e S = Secondary

870-14, Rev . AF

Frequencies are a l l o c a t e d as shown below:

IRIS S tage = 2227.0 MHz MAGE-1 S t age = 2280.0 MHz LAGEOS-2 S/C = NONE

The below:

suppor t parameters f o r t h e Telemetry and Tracking Systems are l is ted

Telemetry MAGE-IS Stacre

IRIS Staae

Transmi t t e r f requency 2280 MHz 2227.0 MHz Format PSK/PCM/NRZ-L PSK/PCM/NRZ-L S u b c a r r i e r f requency 512 kHz 102 4 kHz B i t r a t e 2000 b/s 2000 b /s Record Requ i red Required

Tracking

Transmi t t e r RF s i g n a l

Support

Antenna ra te Angle d a t a Recording DSN NAV

Beacon, S-band N / A 0.3 W 5 w

E a r t h o r b i t a l E a r t h O r b i t a l Required Required Analog required Analog Required Required Required

The a l l o c a t i o n of r e s p o n s i b i l i t i e s f o r t r a c k i n g suppor t i s l is ted i n t h e fo l lowing table:

. . . . I Phase Suppor t Respons ib i l i t v

STS Launch Trans fe r and F i n a l Burns O r b i t F i n a l O r b i t Laser Ranging

TDRS S ESA/DSN/DOD

DSN GSFC

870-14, Rev. AF

TDS Mgr: A . Berman NOPE: A . Short

Project Mgr: A. Spear (JPL) Mission Dir: J. Scott

LV/Range: STS-TBS/ETR

Launch Date: May 4, 1989 proiected SC Life/DSN SuDDort: 3 years/3 years

Project Resoonsibility: Jet Propulsion Laboratory (JPL) I . .

Source: SIRD January 1987/NSP May 1988 Sponsor: O S 0

A . MISSION DESCRTPTION

The Magellan mission consists of a single spacecraft to be placed in an elliptical orbit about Venus. The main objective of the mission is to perform radar imaging, altimetry, and reflectivity of 90% of the planet for one Venusian year (243 days).

B. FLIGHT PROFILE

The Magellan spacecraft and inertial upper stage (IUS) were deployed via the Space Transportation System (STS) on May 4, 1989. Following deployment, the IUS placed the spacecraft on a planetary injection trajectory for Venus. Venus Orbit Insertion (VOI) of the Magellan Spacecraft is scheduled €or August 10, 1990.

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

(a) 1"I;Lssion Phase Period

(b) Launch 4/89

Passes/Month

26-m 34-m STD

34-m STD Early Cruise 5/89

Cruise 6/89-6/90

12 60 12

34-m HEF 34-m STD 70-m

Cruise

VOI/IOC

Mapping

9/90-12/90

70 70-m

90 70-m

3 4 -HEF 70-m

Mapping 1/91/-5/15/91 90 90

34-m HEF 34-m STD

Extended Mission Mapping 5/ 15/ 91 -1 / 95 90 34-m HEF

2. Network Support

the following The support provided by the DSN is indicated in table :

Svstem Gobdstone Ganberra

12 14 15 16 42 4 3 45 46

I%adLid

61 63 65 66

S-band VLBI . P P

X-band VLBI P P P P

S-band TLM P P * P P *

X-band TLM P P P P P P

S-band CMD P P * P P *

X-band CMD P * P

S-band TRK P P * P P

NOTES: P = Prime *Initial acquisition only.

870-14, Rev . AF

Frequencies a r e a l l o c a t e d accord ing t o t h e fo l lowing table:

Svstem ( M W P o l a r i z a t i o n

S-band TLM -- 2297 9 L I N or RCP

X-band TLM -- 8425 - 8 RCP

S-band CMD 2116.0 -- L I N o r RCP

X-band CMD 7171.5 RCP

S-band TRK -- 2297.9 L I N o r RCP

X-band TRK -- 8425.8 RCP o r L I N

The suppor t parameters f o r t h e Telemetry, Command, and Support Systems are l isted below:

Telemetry

Data Streams 2 Format PCM (NRZ-L) /PSK/PM S u b c a r r i e r Frequency 22.5. 360, 960 KHz B i t R a t e 40, 1200 b/s and 11 Record Requ i red

Command

Format PCM/PSK/PM B i t Rate 7.8125 o r 62.5 b/s S u b c a r r i e r Frequency 1 6 KHz sinewave

Support

Uplink Power Antenna R a t e Antenna Angle Data Antenna Autotrack Doppler Rates Recording . Analog . D i g i t a l

-2 , 268.8 kb/s

TBS TBS TBS N o t Required TBS

TBS Required

870-14, Rev. AF

, I . ort Re-

STS Launch IUS Deployment Planetary Mission

TDRS S TDRSS DSN

870-14, Rev. AF

MARS OBSERVER J

TDS Mgr: M. R. Traxler NOPE: T. Howe

Project Mgr: D.D. Evans Mission Mgr: S. Dallas

Launch: September 16, 1992 Proiected SC L ife/DSN Support : 5 years/5 years

Project ResponsibddLy : Jet Propulsion Laboratory . I ,

Source: SIRD and Mission Plan Sponsor: OS0

The Mars Observer mission will deliver a single spacecraft to Mars for an extended orbital study of the planet surface, atmosphere, and gravitational and magnetic fields.

B. FLIGHT PROFILE

The spacecraft will be launched during the September-October 1992 Mars opportunity using a Titan-TOS launch vehicle. The best mass performance for the 1992 opportunity is obtained with a long interplanetary trajectory, with a transit time to Mars of approximately one year. Insertion of the spacecraft into orbit at Mars will be accomplished by a sequence of propulsive maneuvers. The mapping mission will be conducted from a mapping orbit that is nearly circular at low altitude (378 km) and sun synchronous at the desired solar orientation. Repetitive observations of the planet's surface and atmosphere will be conducted throughout the primary mission, which extends for one Martian year (687 days from start of Mapping Phase).

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

Coverage g o a l s f o r t h e launch, cruise, o r b i t i n s e r t i o n , and mapping phases a r e l isted below:

Passes / Month Antennas * I ission Phase

Launch Continuous 9/16/92 - 10/9/92 2 Coverage 30 days 60

2 6m 34m HEF

Ea r ly C r u i s e 10/92 (15 days) 60 4

34m HEF 7 Om

Cru i se 10/92 - 2/93 35 4

34m HEF 7 Om

Gravi ty Wave 3/93 - 4/93 60 4

34m HEF 7 Om

Approach Phase 5/93 - 6/93 60 15

34m HEF 7 Om

Close Approach Phase 7/93 90 30

34m HEF 7 Om

MOI 8/93 90 12

34m HEF 7 Om

Orb i t I n s e r t i o n 9/93 - 12/15/93 90 34m HEF

Mapping Phase 12/16/93 - 4/94 30 10

34m HEF 7 Om

Mapping Phase 5/94 58 34m HEF 28 70m HEF

Mapping Phase 6/94 40 34m HEF 7 Om

Mapping Phase 7/94 - 12/94

Mapping Phase 1/95

40 34m HEF

34m HEF 7 Om

Mapping Phase

MBR Phase

2/95 - 9/24/95

9/25/95 - 11/19/95

40 34m HEF

34m HEF 7 Om

Mars ‘94 11/20/95 - 2/3/96 Landed Packages

30 KEF

870-14, Rev. AF

2. Network Support

The suppor t provided by t h e DSN i n t h e launch phase and i n t h e e a r l y c r u i s e phase is i n d i c a t e d i n t h e fo l lowing t a b l e :

1 4 15 16 43 45 46 63 65 66

X-band TLM P P P

X-band CMD & Radio P M e t r i c Data

NOTES: P = P r i m e * 26-m X-band suppor t f o r i n i t i a l a c q u i s i t i o n

The suppor t provided by t h e DSN i n t h e cruise phase through EOM is i n d i c a t e d i n t h e fo l lowing t a b l e :

14 15 16 43 45 46 63 65 66

X-band TLM P P P P P P

X-band TLM (CP) P P P

X-band CMD & P Tracking D a t a

X-band TRK P P P

NOTES: P = P r i m e (CP) = C r i t i c a l Periods

3. Compa t ib i l i t y T e s t s

Compa t ib i l i t y t e s t i n g w i l l be suppor ted by CTA 2 1 and MIL 71. Prelaunch suppor t w i l l be provided by MIL-71, s t a r t i n g a t launch minus 5 months.

870-14, Rev. AF

Frequencies assigned to the Mars Observer Spacecraft are given in the following table:

Svstem URlink C M W Downlink CMHz) Polarization

Command X-band -

Transponder 7164.624229

Telemetry --

Transponder --

Radio Metric X-band

ADOR --

- RCP (low-gain antenna) / (high-gain antenna)

8417.716050

8423.148147

X-band

8423.14814

(1 Telemetry

Data Streams 1 Modulation PCM (NRZ-L) /PSK/PM Subcarrier 320 kHz, 2 1 . 3 3 3 kHz Science and engineering 4, 8 , 1 6 , 2 1 . 3 3 3 4 , 32 , 40, data plus Reed-Solomon 42.6677, 64, 80 , 8 5 . 3 3 3 4 kb/s encoding (Symobs/Sec)*

Engineer data (bits/sec) 10, 250, 2000, 8000, l6,OOO, 3 2 , 0 0 0 Coding Convolutional (R=1/2; K=7) Mod Index Selectable

*Convolutional coding is also added, which will double the symbols transmitted to the ground.

870-14, Rev.' AF

(2) Command

Modulation PCM/PSK/PM Subcarrier Frequency 16 kHz Bit Rates 500, 250, 125 (Nominal), 62.5,

31.25, 15.6, or 7.8125 b/s (emergency)

(3) support

DSN Transit Power 20 kW Angular Rate Planetary, except for initial near-

ADOR and ADOD Yes Radio Science Planetary occultations (687 days)

and mass gravity information from radio metric data

Earth requirements and cruise

* . . I . ission Phase port Resoonsibilitv

Launch (Titan/TOS) Injection Cruise/Planetary

Launch Vehicle DSN DSN

870-14, Rev. AF

(Re 5 m bu r sa ble)

TDS Mgr: N. Fanelli NOPE: R. E. Nevarez

Project Mgr: T. Hayashi (ISAS) MOM: T. Nishimura (ISAS)

Launch Date : January 24, 1990 Projected SC I,ife/DSN Sutmort : 1 year/9 months

Project Responsibilitv: Institute of Space and Astronautical Science (ISAS) * I ,

Source: SIRD April 1989 Sponsor: ISAS

The MUSES-A spacecraft mission objectives are to study the effect of a double lunar swingby technique, lunar orbital insertion, obtain experience using optical navigation equipment, measure mass and momentum of micrometeorids by using a particle dust counter, and to support a packet telemetry and Reed-Solomon coding experiment by using a newly developed fault tolerant onboard computer.

B. FLIGHT PROFILE

MUSES-A was launched on a MU-311-5 launch vehicle from Kagoshima Space Center (KSC) in Uchinoura, Kagoshima Prefecture, Japan with a launch angle of 79 deg in elevation and 90 deg in azimuth. The burn of the 4th stage motor injects the spacecraft into the mission orbit of 200 km perigee, 350,000 km apogee, and 30 deg inclination. The spacecraft is spun up to 2 rev/s prior to

Y 30-1

870-14, Rev. AF

injection. After separation, the RCS maneuver was performed reducing the spin rate to 20 rev/min. Prior to the first swingby maneuver a tiny satellite (12 kg), which is carried aloft on the top of the main spacecraft, was injected into lunar orbit.

C. COVERAGE

No DSN launch vehicle support was required. The DSN will support the Mission phase only.

1. Coverage Goals

The DSN supports the Mission phase, providing downlink telemetry recording at all stations until one of the stations completes its second contact with the spacecraft. The DSN also provides radiometric data acquisition and orbit determination for each lunar swingby maneuver. This will involve five or six passes of about 6 hours duration. There is no requirement for DSN commanding.

2. Network Support

Svsltem Goldstone Canberra Madrid

12 14 15 16 42 43 45 46 61 63 65 66

S-band TLM P P P

S-band TRK P P P

NOTES: P = Prime B = Backup

Svstem golink ~PIHzl P o l a r i z a t i o n

S-band TLM N/A

S-band CMD N/A

2259.9

S-band TRK 2081.0 2259.9 RCP

870-14, Rev. AF

Te 1 emet ry

Data Streams Format

Subcarrier Frequency Bit Rates Record

Command

support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Formats

1 PCM (NRZ-S) /BiPI/PM or PCM (NRZ-S) PSK/PM 8192 Hz (256 b/s) 256, 2048, and 8192 b/s Required

PCM (PN/Big) PSK/PM 8000 Hz 1000 Hz

1 to 10 kw Mode rate Required Required ( 2 6 -m only) Modest Tone (Prime) (500 kHz Major Tone) DSN Standard (Backup)

Required Required

a . . . I Support Responsibility ission Phase

Prelaunch Launch Mission

I SAS I SAS DSN, ISAS

870-14, Rev. AF

NI MB US-7

Project Mgr: P. Pashby (GSFC) MOM: M. Foreman (GSFC)

Launch Date: Oct. 24, 1978 Projected SC Life/DSN Support: 15 years/ll years

Proiect Responsibility: Goddard Space Flight Center (GSFC)

Source: SIRD August 1983/NSP Sponsor: O S 0

The Nimbus program provides for the research and development of a series of large automated spacecraft for the flight test of advanced instruments for pollution, oceanographic, and meteorological applications. The basic spacecraft is attitude-stabilized in three axes, with the yaw axis always pointing towards the center of the Earth. The spacecraft provides a stable platform, power, command, and data handling support for active and passive sensors for daily global surveillance of the atmosphere, and for mapping details of the atmospheric structure and the Earth surface from satellite altitudes. The primary objectives of the Nimbus-7 mission are as follows:

(1) To observe gases or particulates in the troposphere to determine the feasibility of mapping sources, sinks, and dispersion mechanisms of atmospheric pollutants.

870-14, Rev. AF

(2) To observe ocean color, temperature, and ice conditions, particularly in coastal zones, with sufficient spatial and spectral resolution to determine the feasibility of applications such as detecting pollutants on the water surface; determining the nature of materials suspended in the water; applying the observations to the mapping of sediments, biologically productive areas, and interactions between coastal effluents and open ocean water; and demonstrating improvement in ship route forecasting.

B. FLIGHT PROFILE

To provide daily global coverage, the Nimbus-7 spacecraft was launched October 24, 1978 into a nominally circular Sun-synchronous orbit at an altitude of approximately 955 km. The inclination of the orbit plane was established at a value (approximately 99 degrees) such that orbital precession keeps the local time of equator crossing at 1200 local time, northbound. The nominal altitude and time of equator crossing was selected to meet experiment requirements for geographical resolutions, coverage, and data acquisition.

C. COVERAGE

The DSN began support on February 1, 1985.

1. Coverage Goals

Coverage will be provided through end of mission and will consist of twelve 15-minute passes per day. (The minimum requirement is nine 15-minute passes per day.)

2. Network Support

12 14 15 16 42 43 45 46 61 63 66

S-band TLM

S-band CMD

S-band TRK

NOTE: P = Prime

870-14, Rev. AF

Svstem

S-band TLM -- 2211.0 (Link 1) RCP -- 2273.5 (Link 2) RCP

S-band CMD 2093.5 -- RCP

S-band TRK 2093.5 2273.5 RCP

E. SUPPORT PARANETERS

(1 ) Telemetry

Data Streams 3 Format (Link 1)

(Link 2) Subcarrier Frequency (Link 2) Bit Rates (Link 1)

(Link 2) Coding Record

(2) Command

(3) Support

Uplink Power 2 kW (nominal) Antenna Rate High Antenna Angle Data Antenna Autotrack Doppler Rates

PCM (SP-L) /FM PCM (SP-L) /PSK/PM and PCM (SP-L) /PM 1560 kHz 800 kb/s 4 kb/s and 800 kb/s None Required

PCM (NRZ -L) / P SK-Summed/FM/PM 2 kHz PSK, 70 kHz FM 1000 b/s

TBD Required TBD

Range Format Tone on 70 kHz subcarrier Recording . Analog Required . Digital Not required

870-14, Rev. AF

Earth Orbit STDN (through Jan. 1985) DSN (after Jan. 1985) STDN BLT (after Jan. 1985)

The international GPS global network consists of six stations, all of which are equipped with GPS receivers and their connections to communication links with the appropriate operations center. For this mission the operations center is at JPL. Three of the sites are at the existing deep space stations, namely Goldstone, California, Tidbinbilla, Australia, and Robledo, Spain. The additional three sites are at Usuda, Japan, which is the location of its 64-m deep space station; Hartebestock, South Africa, which operates by French network stations with headquarters in Toulouse, France. For this project the interface for the data from South Africa is at Toulouse. The third site is at the former STDN complex 35 miles north of Santiago, Chile. The three sites will be covered by memorandums of agreements between NASA and the indigenous agencies, namely Institute of Space & Astronautical Sciences, Tokyo, Japan; the French network (CNES), which will be responsible for acquiring the data in South Africa and transmitting it to NASA JPL; and the University of Chile in Santiago, which has acquired all of the NASA STDN facilities and will maintain and operate the NASA equipment on loan and transmit the data to NASA JPL.

The JPL DSN will assume the lead role as "GPS Network Coordinator," with responsibility to initiate, facilitate, negotiate, and otherwise successfully execute all joint network operational aspects, including planning, documentation, configuration, communications, and monitor and control, of the joint DSN-International Agencies GPS Six-Station Network.

870-14, Rev. AF

OCEAN TOPOGRAPHY EXPERIMENT (TOPEX/POSElDON)

5@3 d i (Emergency Support) a,f

TDS Mgr: A . L. Berman NOPE: A . Short

Project Mgr: C. A. Yamarone

LV/Range: Ariane/CSG MOM: R. A. Stiver

Launch Date : July 1, 1992 projected SC Life/DSN Support: 5 years/5 years

Project Responslbilitv . I . : Jet Propulsion Laboratory (JPL)

Source: SIRD Rev. A, January 1990/NSP late 1990 Sponsor: OS0

The TOPEX Mission consists of a single TOPEX spacecraft which will be placed in a high Earth circular orbit, with an altitude of 1334 km and a 63-deg inclination. Earth tracks will repeat every 10 days. Using an altimeter, TOPEX will map the topography of the ocean's surface to obtain scientific data for use in determining global ocean circulation patterns.

Of particular interest to JPL is the Global Positioning Satellite (GPS) demonstration. Receivers and media calibration equipment at the DSS Media Calibration Subsystem at the three DSN complexes will augment the GPS system to provide a differential GPS data type, which will be used for precision orbit determination. With three DSN sites, 15-cm accuracy is anticipated. If three additional sites are acquired, >10-cm accuracy is expected.

870-14, Rev. AF

B. FLIGHT PROFILE

The TOPEX spacecraft will be launched from the Centre Spatiales de Guiana in French Guiana on an Ariane launch vehicle.

C. COVERAGE

1. Coverage Goals

Emergency support will be provided by the DSN 26-m subnet as required for backup support of TDRS.

2. GPS Space Vehicle Coverage

The DSS Media Calibration Subsystem will provide continuous coverage of the constellation of GPS Space Vehicles (GPSss-SV). The constellation will have between 18 and 24 satellites.

3. TOPEX GPS Receiver Coverage

Radio metric data acquired by the GPS Receiver on TOPEX comes to JPL through the TDRS telemetry link.

Svstem Uplink IM Hz 1 Qownlink IMHz) Polarization

GPS L2 -- 1227.60 RCP

1575.4 RCP GPS L1 --

All GPS Space Vehicles (SV) transmit on the same two frequencies. Each GPS SV is assigned unique orthogonal PN codes that modulate the carriers and allow a ground receiver to separate the signals from individual GPS SVs.

870-14, Rev. AF

E. TRACKING SUPPORT RESPONSIBILITY

' . . . I ission Phase port Responsbility

Ariane Launch High Earth orbit Emergency Support GPS Demonstration Support

GSG TDRS DSN DSN

870-14, Rev. AF

PIONEER 6 THROUGH 8

TDS Mgr: A. Berman NOPE: L. Shaw

Project Mgr: R. Fimmel (ARC) MOM: D. Lozier (ARC)

Jlaunch Date: Dec. 16, 1965 - Aug. 17, 1966 - Dec. 13, 1967 Projected SC Life/DSN Support: 10 years/through 1993

p ro i e c t Re s ~ o n s ibilitv: Ames Research Center (ARC)

Source: SIRD September 1983/NSP June 1984 Sponsor: O S 0

The primary objective of the Pioneer 6 through 8 missions is to collect scientific data relative to interplanetary phenomena within a range of approximately 0.8 to 1.2 astronomical units (AUs) from the sun. Phenomena of particular interest include the characteristics of electric and magnetic fields, electron density along the Earth-spacecraft path, and temporal and spatial distribution of plasma, cosmic rays, high-energy particles, and cosmic dust.

B. FLIGHT PROFILE

Each of the Pioneer spacecraft were launched into heliocentric orbit by Delta launch vehicles. Following injection, each spacecraft was oriented with its spin axis normal to the ecliptic plane so that the solar panels would be fully illuminated and the high-gain antenna pattern would be aligned with Earth's orbit.

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

N o r o u t i n e coverage i s planned. Spec ia l even t s of s c i e n t i f i c interest are suppor ted when t i m e i s a v a i l a b l e .

2. Network Support

The suppor t p rovided by t h e DSN i s indicated i n t h e fo l lowing t a b l e :

12 1 4 1 5 1 6 42 43 45 46 6 1 63 66

S-band TLM B P

S-band CMD B P

S-band TRK B P

NOTE: P = P r i m e ; DSSs 1 2 , 42, and 6 1 are a b l e t o provide suppor t du r ing c e r t a i n o r b i t a l periods. B = Backup

Frequencies a re a l located accord ing t o t h e t a b l e below.

Svstem Downlink (MH Z)

S-band TLM -

S-band CMD 2110.9251541 2110.584105

2292.407407 2292.407407

S-band TRK 2110.9251541 2292.407407/ 2110.584105 2292.037037

N o t e : P ioneer 6 : 2292.037037 and 2110.584105, only

p o l a r i z a t i o n

Linear

The suppor t parameters f o r t h e Telemetry, Command, and Support Systems a r e l i s ted below:

870-14, Rev. AF

(1 ) Telemetry

Data Streams Format Subcarrier Frequency Bit Rates Record Coding

( 2 ) Command

Format Bit Rate Subca rrie r Frequency

( 3 ) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Auto Track Doppler Rates Range Format Recording . Analog . Digital

1 PCM (NRZ-L) /PSK/PM 2048 H z 8, 16, 64, 256, 512 b/s Required Convolutional, K = 25, R = 1 / 2

PCM/FSK/PM 1 b/s 150 and 240 Hz

20 kW Side real Not required Not required Mode rat e Not applicable

Not required Required

Planet a ry D SN

870-14, Rev. AF

870-14, Rev. A F

PONEER 10 AND 11

TDS M g r : A. Berman NOPE: A. Shor t

P r o j e c t M g r : R. Fimmel (ARC) MOM: D . Loz ier (ARC)

Launc h Da te : Pioneer 1 0 - March 2, 1972; Pioneer 11 - Apr i l 5, 1973 P r o j e c t e d SC Life/DSN SUpDOrt : December 1996/December 1995

: h e s Research Center (ARC) P r o j e c t R e s p o n s i b i l i t v . a .

The primary o b j e c t i v e of t h e P ioneer 1 0 and 11 miss ions i s t o i n v e s t i g a t e t h e i n t e r p l a n e t a r y medium beyond t h e o r b i t of Sa turn and, i n p a r t i c u l a r , t o g a t h e r d a t a which may l o c a t e t h e he l iopause as t h e s e s p a c e c r a f t c r u i s e ou t of t h e s o l a r system t o t h e extreme of t h e i r communication c a p a b i l i t i e s .

B. FLIGHT PROFILE

A f t e r i t encountered J u p i t e r i n 1973, P ioneer 1 0 began i t s d e p a r t u r e from t h e s o l a r system i n t h e d i r e c t i o n of t h e s o l a r apex. P ioneer 11 encountered J u p i t e r i n 1974 and Sa turn i n 1979; it a l s o w i l l l e a v e t h e s o l a r system, b u t i n t h e oppos i t e d i r e c t i o n of P ioneer 1 0 .

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

Phase Period Passes/Month Antennas . I

Pioneer 10 Cruise 1 / 8 9-1 / 95 60 7 Om

Pioneer 11 Cruise 10/89-1 /95 60 70-m

2. Network Support

1 2 1 4 1 5 1 6 42 43 45 46 6 1 63 66

S-band TLM P P P P P P

S-band CMD P P P P P P

S-band TRK P P

NOTE: P = Prime

P P P P

Svstem Uplink (MHz) Polarization

S-band TLM - 2292.407407 2292.407407

S-band CMD 2110.584/ - 2110.925

S-band TRK 2110.5841 2110.925

2292.037037/ 2292.407407

870-14, Rev. AF

(1) Telemetry

Data Streams Format Subcarrier Frequency Bit Rate

Record Coding

( 2 ) Command

Format Bit Rate Subcarrier Frequencies Subcarrier Waveform

( 3 ) Support

1 PCM (NRZ-L) /PSK/PM 32 kHz 16, 32, 64, 128, 256, 512, 1024, 2048 b/s Required Convolutional, K = 32 R = 1/2

PCM/FSK/PM 1 6 b/s (equivalent) 128.0, 204.8 Hz Sine

10 to 20 kW Si de re a 1 Not required Not required Moderate None

Support Responsibility . * . M-

P1 anet ary DSN

870-14, Rev. AF

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870-14, Rev. AF

PIONEER 12 (PN-12)

TDS Mgr: A . Berman NOPE: L. Shaw

Project Mgr: R. Fimel (ARC) MOM: D. Lozier (ARC)

Jaunch Dab: May 20, 1978 Proiected SC L ife/DSN SUDDO rt: August 1992/August 1992

Proiect Responsibilitv: Ames Research Center (ARC)

The Pioneer 12 investigates the atmospheric characteristics of Venus and the region about the planet. Additionally, the spacecraft performs altimetry and planetary imaging.

B. FLIGHT PROFILE

The Pioneer 12 spacecraft is in a 24-hour elliptical orbit about Venus. Atmospheric and altimetry data are obtained mainly around periapsis, and planetary imaging is normally performed around apoapsis. The spacecraft is expected to enter the Venusian atmosphere in 1992.

870-14, R e v . AF

C . COVERAGE

. . i s s i o n Phase

O r b i t

Period

1/89-8/92 1/89-8/92

PassesLMonth Antennas

60 34-m STD 3 70-m

2. N e t w o r k Support

T h e support provided by t h e DSN i s indicated i n t h e fo l lowing t ab le :

12 14 15 16 42 43 45 46 61 63 66

S-band TLM P P B P P P P

S - b a n d CMD P B P P P

S-band TRK P B P P P

X - b a n d TRK P B P P P

NOTE: P = P r i m e ; B = B a c k u p

Frequencies are al located according t o t h e f o l l o w i n g table:

Svstem Y- H Downlink (MHz) P o l a r i z a t i o n

S-band TLM - 2293.888 o r 2294.259 RCP / L i n e a r

S - b a n d CMD 2112.289 o r 2112.630 - R C P / L i n e a r

S-band TRK 2112.289 or 2112.630 2293.888 o r 2294.259 R C P / L i n e a r

X - b a n d TRK - 8410.925 o r 8412.283 RCP

870-14, Rev. AF

The suppor t parameters f o r t h e Telemetry, Command, and Support Systems a r e listed below:

(1 ) Telemetry

D a t a Streams 1 Format PCM (NRZ-L) /PSK/PM Subca rrier Frequency 16 kHz B i t R a t e 8, 16, 32, 64, 128, 170.66, 256,

Record Required 341.33, 512, 682.66, 1024, 2048 b/s

(2) Command

Format PCM/FSK/PM B i t R a t e 4 b / s Subca r r i e r Frequency 1 0 0 , 250 Hz

(3) Support

Uplink Power Antenna Rate Antenna A n g l e Data Antenna Autotrack Doppler

. Range

. Rate Recording

. Analog

. D i g i t a l

1 0 t o 1 0 0 kW S ide rea 1 Not r equ i r ed Not r e q u i r e d (Conscan f o r X-band)

+210 kHz 50-150 Hz

Not r e q u i r e d R e q u i r e d

The a l l o c a t i o n of r e s p o n s i b i l i t i e s f o r t r a c k i n g suppor t i s l isted i n t h e fo l lowing table:

9 . I . . Phase Support Respons&l l i t y

P l a n e t a r y D S N

870-14, R e v . AF

(This page intentionally l e f t blank.)

870-14, Rev. AF

ROENTGENSATELLIT / (ROSAT)

TDS Mgr: M. Traxler NOPE: T. Howe

Project Mgr: G. Ousley (GSFC) MOM: F. Guckenbiehl (GSOC)

LV/Range: Delta II/CCAFS

L- D : June 1, 1 9 9 0 Projected SC Life/DSN Surmor t : 18 months/l8 months

Project Responsibilitv: Goddard Space Flight Center (BMFT Cooperative)

Source: Project Plan (GSFC), dated October 1983, and other project documents Sponsor: O S 0

The ROSAT is an international cooperative program between the National Aeronautics and Space Administration (NASA) and the Bundesdnisterium fuer Forschung and Technologie (BMFT) of the Federal Republic of Germany. Germany will develop and provide a spacecraft with an X-ray telescope featuring two instruments at the focal plane of the telescope, and a stand-alone Wide Field X-ray Camera (WFC) provided by the United Kingdom (U.K.). NASA will provide one instrument: a High Resolution X-ray Imager (HRI) for mounting in the focal plane similar to the High Energy Astronomy Observatory (HEA0)-2 HRI. NASA launched the satellite on a Delta I1 vehicle in June 1990.

36-1 T F

870-14, Rev. AF

ROSAT will make an all-sky survey of X-ray and extreme ultraviolet (EW) sources, using redundant German Position Sensitive Proportional Counters (PSPCs) and the British WFC during the first six months of its orbital mission while in a scan mode. The next 12 months will be dedicated to detailed measurements of selected X-ray sources employing the U.S. HRI, the German PSPC, and the U.K WFC in a stationary or pointing mode of spacecraft operation.

In the scan mode, the spacecraft will maintain the telescope axis approximately normal to the Earth (i.e., one spacecraft rotation per orbit) - In the pointing mode, the spacecraft will be three-axis stabilized with the

to lo4 seconds). telescope pointing to a particular X-ray source for long periods of time (10 3

A Memorandum of Understanding (MOU) setting forth the international agreement between NASA and the BMFT for the joint accomplishment of the ROSAT program was signed on August 8, 1982.

B. FLIGHT PROFILE

The ROSAT was launched from the Cape Canaveral Air Force Station on a Delta 2 expendable launch vehicle and placed in a circular orbit at an altitude of 580 km, with a 53-deg inclination.

C. COVERAGE

1. Coverage Goals

The support planned by the DSN for ROSAT is provided in the following table :

Launch and S/C checkout

Period Passes - Antennas

6/90 60 2 6m

DSN Emergency 6/90 - 12/92 Support Phase

2. Network Support

3 2 6m

The DSN will provide prime support from spacecraft release from the Delta I1 through L + 28 days. The DSN will provide backup support to Weilheim for the duration of the mission. This support will normally be provided by the DSN 26-meter stations, and will only be provided as specifically required by the project, German Space Operations Center. The support provided by the DSN is indicated in the following table:

870-14, Rev. AF

Svstem

S-band TLM

S-band CMD

Goldstone Canberra

1 2 1 4 15 1 6 42 43 45 46

S-band TRK P/B P/B

NOTE: P/B = Prime or backup depending on mission phase

Madrid

6 1 63 66

The uplink and downlink frequencies are listed below:

Uplink : 2096.27 MHz Downlink: 2276.50 MHz (RCP or LCP)

The support parameters for the Telemetry and Command Systems are listed below:

(1 ) Telemetry

Data Streams: 2 ( 8 kb/s only supported by DSN)

Modulation : PCM/BIgL/PM Subcarrier : None (Directly on Carrier) Bit Rates : 8 kb/s by DSN

1 Mb/s science data supported only by Weilhelm

( 2 ) Command

Modulation : PCM/PSK/PM Subcarrier Frequency: 1 6 kHz Bit Rate : 1 kb/s

Delta I1 Launch to Orbit Prime Spacecraft Mission Support Backup Spacecraft Mission Support

GSFC Weilheim/DSN* DSN

*Selected prime support €or the first four weeks after launch.

870-14, Rev. AF

SAMPEX

Launch Date : June 1992 Proiected SC Life/DSN Support:

Project Mgr: MOM :

LV/Range:

Prime mission 3 years mission/two 15 minute backup to Wallops for dump.

P 2 v : Goddard Space Flight Center I , .

G. Colon J. Catena Scout/VAFB

plus 3 years extended contacts per day, and high rate telemetry data

(GSFC)

Source: SIRD Sponsor: OS0

GSFC developed the SMEX program, managed by the Special Payloads Division (SPD) (Code 7 4 0 ) , to provide frequent flight opportunities for highly focused and inexpensive space science missions. SMEX was conceived as a low- cost program with a short turnaround ( 3 years) from mission selection until launch. SAMPEX is the first mission of the SMEX program. Its primary scientific objectives are to measure the elemental and isotopic composition of solar energetic particles, anomalous cosmic rays, and galactic cosmic rays over the energy range from approximately 1 to several hundred MeV per nucleon. By determining the dependence of the fluxes on geomagnetic cutoff rigidity over the polar orbit, the ionization state o f the anomalous component will be determined, along with the mean ionization state o f solar energetic particles. The dependence of these fluxes on the solar activity cycle will be measured by carrying out continuous observations over an extended (3-year) portion of the current activity cycle. A further primary objective is to

870-14, Rev. AF

determine flux levels and local time dependence of relativistic precipitating magnetospheric electrons during a period of declining solar activity.

B. FLIGHT PROFILE

SAMPEX will be launched June 1992, using a four-stage Scout launch vehicle into a nominal elliptical orbit of 450 by 850 kilometers with an inclination of 82 degrees (not Sun-synchronous) from VAFB. There is no transfer orbit for the SAMPEX spacecraft.

Using this Scout configuration, the uncertainty in achieving the perigee and apogee are as follows for a (TBS) percent probability.

1. Period = 98 minutes

2. Contact time = 8 - 16 minutes

C. COVERAGE

1. Coverage Goals

DSN will support two contacts per day (12 hours apart), low rate TLM, command, and RMD. Provide backup support to Wallops for high rate TLM dumps.

2. Network Support

Svstem Goldstone Canbe rra Madrid

12 14 15 16 17 42 43 45 46 61 63 66

S-band TLM

S-band CMD

S-band TRK P B

NOTE: P = Prime B = Back-up

Scheduled for August 15, 1991.

870-14, Rev. AF

S-band TLM 2215.0 LCP

S-band CMD 2 .039 .65 LCP

S-band TRK 2215.0 LCP

(1) Telemetry

Data Streams Format Subcarrier Bit Rates Record

(2) Command

(3) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Format

3 PCM/NRZ-L/CONVL K=7, R=l/Z/Bi@-L/PM None (Directly on Carrier) 4, 1 6 , and 900 kb/s Digital

PCM/NRZ-L/PSK/PM 2 .0 kb/s 1 6 kHz/s

2 kW Nominal Moderate Required Required

Tone (Sine)

Recording . Digital

Launch Mission Emergency

GSFC DSN DSN

870-14, Rev. AF

SOLAR-A

TDS Mgr: J. A. Goodwin NOPE: R. E. Nevarez

Project Mgr: Y. Ogawara (ISAS) MOM: K. Ninomiya (ISAS)

Jaunt h Date : August 16, 1991 cted SC L ife/DSN Support : 3 yearsl2 years

proiect ResDons ibilitv : Institute of Space and Astronautical Science (ISAS)

Source: Preliminary S I m September 1990 Sponsor: ISAS

The SOLAR-A spacecraft mission objectives are to investigate high energy phenomena of the Sun using X-ray telescopes and spectrometers during the maximum activity period of the solar cycle. Experiments are being supported by various Universities and Laboratories in Japan, England, and the United States.

B. FLIGHT PROFILE

The spacecraft will be launched from Kagoshima Space Center (KSC) in Uchinoura, Kagoshima Prefecture, Japan into a circular Earth orbit of approximately 500 km altitude and 31 deg inclination by a M3SII launch vehicle resulting in a 97-min orbit duration.

38-1 FIL

870-14, R e v . A F

C . COVERAGE

N o DSN launch vehicle support i s required. T h e DSN w i l l support t h e Mission phase only.

T h e DSN w i l l record downlink te lemet ry and t r a n s m i t t h e data i n rea l t i m e t o I S A S . T h e project r e q u i r e m e n t i s t o support 10 contac ts w i t h the spacecraft per day dur ing t h e first year of t h e p r i m e m i s s i o n . Support r e q u i r e m e n t s w i l l be assessed on a yea r ly basis a f t e r t h e f i r s t year. S t a t i o n v i e w p e r i o d s w i l l be 7 t o 1 0 m i n u t e s .

T h e support provided by t h e DSN i s indicated i n t h e f o l l o w i n g table:

Svstem Goldstone Ganberra Madrid

S-band TLM

S-band CMD

S-band TRK

NOTE: P = P r i m e

12 14 15 16 42 43 45 46 61 63 66

S v s t e m U p l i n k (MHz) D o w n l i n k (MHz 1 P o l a r i z a t i o s l

S-band TLM N/A TBS RCP

S-band CMD N/A N/A N/A

S-band TRK N/A N/A N/A

870-14, Rev. AF

The support parameters for the Telemetry, Command, and Support Systems -are listed below:

(1) Telemetry

Data Streams 1 Format PCM(NR2-S) Bi@/PM or

Subcarrier Frequency 524000 Hz Bit Rates 1024, 4096, and 32768 b/s

PCM (NRZ-S) PSK/PM

(Rea 1 - t ime ) 131072 coded and 262144 b/s uncoded (Playback)

Coding Convolutional, K=7 R=1/2 Record Required

( 2 ) Command

Format PCM (NRZ-L) /PSK/PM Subcarrier Frequency TBS Bit Rate 4000 b/s

(3) Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Formats Re c o rdi ng

. Analog

. Digital

1 to 10 kW Moderate Required Required (26-m only) Modest N/A

N/A Required

Support Responsibility a , . Mission p hase

Prelaunch Launch Mission

I SAS I SAS DSN, ISAS

870-14, Rev. AF

SPACE FLYER UNIT (SFW

(Reimbursable)

TDS M g r : J. P . Goodwin NOPE: R. Nevarez

P r o j e c t M g r : K . Kur ik i (ISAS) MOM: T. Ninomiya (ISAS)

U u n c h D a t e : January 1, 1994 P r o j e c t e d SC Life/DSN SUpQOrt: Reusable/G months

P r o j e c t Reswons ib i l i tv : I n s t i t u t e of Space and A s t r o n a u t i c a l Science (ISAS) , I ,

Source: SIRD Sponsor: ISAS

The Space F l y e r Unit (SFU) i s an unmanned, reusable , and r e t r i e v a b l e f r e e - f l y i n g p l a t fo rm f o r mult ipurpose use. SFU i s t o be launched by an H - I 1 launch v e h i c l e i n t o a low-Earth o r b i t of 4 0 0 t o 500 km. The s p a c e c r a f t w i l l c a r r y seven i n d i v i d u a l experiments t o be completed du r ing i t s miss ion pe r iod . Upon completion, t h e SFU s p a c e c r a f t i s t o be recovered by t h e space s h u t t l e (STS)

B. FLIGHT PROFILE

The SFU s p a c e c r a f t w i l l be launched on an H - I 1 launch v e h i c l e from Tanegashima Space Center (TASC) i n southern Japan, a planned i n i t i a l o r b i t of 400 km perigee, 500 km apogee.

870-14, R e v . AF

C. COVE RAGE

T h e DSN w i l l support t h e Ea r ly O r b i t phase and the R e t r i e v a l phase i n support of t h e S F U project .

T h e DSN w i l l u s e the 26-m subnet t o support t h e E a r l y O r b i t and R e c o v e r y phases of t h e m i s s i o n . Suppor t w i l l c o n s i s t of t e l e m e t r y , command , and ranging.

T h e support provided by t h e DSN i s indicated i n t h e f o l l o w i n g t ab l e :

Svstem Goldstane Canberra Madrid

12 14 15 16 42 43 45 46 61 63 66

S-band TLM P P P

S-band CMD P P P

S-band TRK P P P

NOTE: P = P r i m e

Svstem U p l i n k (MHz) D o w n l i n k (M H z ) B o l a r i z a t i o n

S-band TLM N/A TBS RCP

S-band CMD TBS N/A RCP

S-band TRK TBS TBS RCP

8 7 0 - 1 4 , R e v . AF

T h e support p a r a m e t e r s f o r t h e T e l e m e t r y , Command, and S u p p o r t S y s t e m s are l i s ted b e l o w :

D a t a S t r e a m s F o r m a t S u b c a r r i e r Frequency B i t R a t e s C o d i n g R e c o r d

( 2 ) Command

F o r m a t Subca r r i e r Frequency B i t R a t e

( 3 ) Support

U p l i n k P o w e r A n t e n n a R a t e A n t e n n a A n g l e D a t a A n t e n n a A u t o t r a c k D o p p l e r R a t e s R a n g e Formats R e c o r d i n g . A n a l o g . D i g i t a l

2 PCM ( B i g - L ) /PSK/PM 1 0 2 4 kHz ( 1 0 0 0 , 16000 H z ) 1 0 0 0 , 16000, 128000 b/s N/A R e q u i r e d

PCM (NRZ-M) /PSK/PM 1 6 k H z 2 0 0 0 b / s

1 t o 1 0 kW Mode r a t e R e q u i r e d R e q u i r e d ( 2 6 -m o n l y ) Modest T o n e ( P r i m e ) (500 kHz Major T o n e s )

N/A R e q u i r e d

T h e a l l o c a t i o n of responsibil i t ies f o r t racking support i s l isted i n t h e f o l l o w i n g table:

Prelaunch Launch M i s s ion

NASDA NASDA DSN, I S A S

870-14, Rev. AF

SPACE TRANSPORTATION SYSTEM (STS)

(Emergency Support)

NSM: N. Fanelli NOPE: R. Nevarez

Project Mgr: L. Nicholson (JSC) MSM: T. Janoski (GSFC)

ND: G. Morse (GSFC) LV/Range: STS/ETR

T,aunch Date : Ongoing (Operational Date - September 29, 1988) Proiected SC Life/DSN Sup- : 10 years/lO years

Project Responsibilitv: Johnson Space Center (JSC) (Flight) I , .

Source: PID July 1979 Sponsor: NASA

The Space Transportation System (STS) is a manned reusable launch vehicle (Shuttle) used to carry into space nearly all of the nation's payloads for military, private industry, universities, research organizations, and foreign governments and organizations.

B. FLIGHT PROFILE

The STS is launched from the Eastern Test Range (ETR). Solid launch rocket engines are separated and recovered downrange for reuse. Landings take place at the ETR or at Edwards Air Force Base.

T 40-1

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

Coverage will be provided by the DSN for the STS during emergencies that would prevent communications between the shuttle and the White Sands TDRSS receiving station. Emergency support would be provided by the DSN's 26- meter subnetwork.

2. Network Support

12 14 15 16 42 43 45 46 61 63 66 S-band TLM E E E

S-band CMD E E E

S-band TRK E E E

NOTE: E = Emergency

Svstem DowriLink W L z l Polari zatios

S-band TLM

S-band CMD 2217.5 2287.5

S-band TRK 2217.5 2106.4

2041.9 2106.4

2041.9 2287.5

870-14, Rev. AF

(1) Telemetry

Data Streams 1 Format PM (FM P/B) Subcarrier Frequency N/A Bit Rates 64, 96, 128, 192, 1024 kb/s Record 1024 kb/s

(2) Command

Format Baseband Subcarrier Frequency N/A Bit Rate 72 kb/s, 32 kb/s

(3) Support

Uplink Power Antenna Rate Antenna Angle Rate Antenna Autotrack Doppler Rates Range Format Recording . Analog . Digital

2 kW High Required Required Moderate Major tone

Required Required

The allocation of responsibilities for tracking support is listed in the following table.

Mission Phase

Launch and Landing

Flight

Support Responsibility . . .

JSC/TDRS

TDRSS Emergency D SN

870-14, Rev. AF

TELECOM (TC2A)

(Reimbursable)

Project Mgr: J. Latour (CNES) MOM: J. Dulac (CNES)

Launch Date: November 1991 Projected SC J,ife/DSN Suplsort: 7 years/7 days

Project Reslso nsibility : Center National d'Etudes Spatiales (CNES)

Source: SIRD July 20, 1990 Sponsor: CNES

The Telecom 2-A (TC2A) mission will provide high-speed data link applications, telephone, and television service between France and overseas territories as a follow-on to the TClA, TClB, and TClC. The satellite will be placed in a geostationary orbit at TBS deg east longtidue.

B. FLIGHT PROFILE

The TC2A will be launched from the Centre Spatial Guyanis in French Guiana on an Ariane launch vehicle. The mission follows the typical injection sequence; i.e., parking orbit, transfer orbit, and drift orbit. Attitude maneuvers wil be performed to orient the spcecraft prior to Apogee Kick Motor (AKM) firings. After the final AKM firing, drift phase orbital and attitude maneuvers will be performed to place the spacecraft in its final geostationary posit ion.

870-14, Rev. AF

C. COVERAGE

The DSN w i l l suppor t t h e t r a n s f e r and d r i f t o r b i t miss ion phases .

1. Coverage Goals

The coverage w i l l c o n s i s t of t h e 26-m antennas a t Goldstone, Madrid, and Canberra as p r i m e suppor t f o r t h e t r a n s f e r and d r i f t o r b i t s . Maximum suppor t w i l l c o n s i s t of two 8-hour t r a c k s per s t a t i o n f o r a 7-day pe r iod , p l u s 1 4 days of cont ingency suppor t .

2. Network Support

The suppor t p rovided by t h e DSN i s indicated i n t h e fo l lowing tab le :

.SYstem Goldstone Canberra Madrid

12 1 4 1 5 16 42 43 45 46 61 63 66 S-band TLM P B P P

S-band CMD P B P P

S-band TRK P B P P

NOTE: P = P r i m e B = Backup

Frequencies are a l l o c a t e d accord ing t o t h e fo l lowing t a b l e :

Svstem Uplink ( M H z ) Downlink (MH Z) P o l a r i z a t i o n

S-band TLM N / A TBS RCP/Linear

S-band CMD TBS N/A RCP/Linear

S-band TRK TBS TBS RCP/Linear

8 7 0 - 1 4 , R e v . AF

T h e support p a r a m e t e r s f o r t h e T e l e m e t r y , Command, and Support S y s t e m s a re listed b e l o w :

T e l e m e t r y

D a t a S t r e a m s F o r m a t S u b c a r r i e r Frequency B i t R a t e s C o d i n g R e c o r d

Command

F o r m a t S u b c a r r i e r Frequency B i t R a t e

Support

U p l i n k P o w e r A n t e n n a R a t e A n t e n n a A n g l e R a t e A n t e n n a A u t o t r a c k D o p p l e r R a t e s R a n g e F o r m a t

R e c o r d i n g A n a l o g

. D i g i t a l

1 PCM (SP-L) /PSK/PM 4 0 9 6 0 Hz 160 b/s N/A R e q u i r e d

PCM (NRZ-L) / P S K / P M 8 0 0 0 Hz 1000 Hz

1 t o 1 0 kW Mode r a t e R e q u i r e d R e q u i r e d (26-m only) Modest T o n e ( P r i m e ) (100 kHz Major T o n e ) DSN Standard ( B a c k u p )

R e q u i r e d R e q u i r e d

T h e a l l o c a t i o n of responsibi l i t ies f o r t r a c k i n g support i s l isted i n t h e f o l l o w i n g table .

I . * . . P h a s e Support R e s p o n s i b i l i t y .

A r i a n e launch CSG

T r a n s f e r / D r i f t O r b i t s DSN

G e o s t a t i o n a r y O r b i t CNES

4 1 - 3

870-14, Rev. AF

TELECOM 2=B (TC2B AND

AND 2-C TC2C)

(Rei m b u r sa ble)

Project Mgr: H. Alvarez (CNES) MOM: J. Dulac (CNES)

haunch Date: March 1992; March 1993 or 1994 Projected SC J,ife/DSN SuDport: 7 years/lO days

Proiect Responsibilitv: Center National d'Etudes Spatiales (CNES) # I .

Source: SIRD July 20, 1990 Sponsor: CNES

The Telecom 2-B and 2-C (TC2B and TC2C) missions will provide high-speed data link applications, telephone, and television service between France and overseas territories as a follow-on to the TC2A. The satellite will be placed in a geostationary orbit at TBS deg east longtidue.

B. FLIGHT PROFILE

The TC2B and TC2C will be launched from the Centre Spatial Guyanis in French Guiana on an Ariane launch vehicle. The mission follows the typical injection sequence; i.e., parking orbit, transfer orbit, and drift orbit. Attitude maneuvers wil be performed to orient the spcecraft prior to Apogee Kick Motor (AKM) firings. After the final AKM firing, drift phase orbital and attitude maneuvers will be performed to place the spacecraft in its final geostationary position.

42-1 'I'

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

The coverage will consist of the 26-m antennas at Goldstone, Madrid, and Canberra as prime support for the transfer and drift orbits. Maximum support will consist of two 8-hour tracks per station for a 7-day period, plus 14 days of contingency support.

2. Network Support

12 14 15 16 42 43 45 46 61 63 66 S-band TLM P B P P

S-band CMD P B P P

S-band TRK P B P P

NOTE: P = Prime B = Backup

Svstem Yplink (MtLzl Downlink (MHZr Polarization

S-band TLM N/A TBS RCP/Linear

S-band CMD TBS N/A RCP/Linear

S-band TRK TBS TBS RCP/Linear

8 7 0 - 1 4 , R e v . AF

T h e support p a r a m e t e r s f o r t h e T e l e m e t r y , Command, and Support S y s t e m s a re l is ted b e l o w :

D a t a S t r e a m s 1 F o r m a t PCM (SP-L) /PSK/PM Subcarrier Frequency 4 0 9 6 0 H z B i t R a t e s 1 6 0 b/s Coding N/A R e c o r d R e q u i r e d

( 2 ) Command

F o r m a t PCM (NRZ-L) /PSK/PM Subcar r ie r Frequency 8 0 0 0 H z B i t R a t e 1 0 0 0 H z

( 3 ) Support

U p l i n k P o w e r A n t e n n a R a t e A n t e n n a A n g l e R a t e A n t e n n a A u t o t r a c k D o p p l e r R a t e s R a n g e F o r m a t

R e c o rdi ng . A n a l o g . D i g i t a l

1 t o 1 0 kW Moderate R e q u i r e d R e q u i r e d (26 -m o n l y ) Modest T o n e ( P r i m e ) ( 1 0 0 kHz Major T o n e ) DSN Standard ( B a c k u p )

N/A R e q u i r e d

F . TRACKING SUPPORT RESPONSIBILITY

T h e a l l o c a t i o n of r e s p o n s i b i l i t i e s f o r t r ack ing support i s l is ted i n t h e f o l l o w i n g table .

. . s . .

Support R e s p o n s i b i l i t y i s s i o n P h a s e

A r i a n e launch CSG

T r a n s f e r / D r i f t O r b i t s DSN

G e o s t a t i o n a r y O r b i t CNES

4 2 - 3

870-14, Rev. AI?

870-14, Rev. AF

TRACKING AND DATA RELAY SATELLITE SYSTEM

(TDRSS)

NSM: N. A. Fanelli NOPE: R. E. Nevarez

Project Mgr: C. Vanek (GSFC)

LV/Range: STS-IUS/ETR MSM: J. McKenzie (GSFC)

Launch Date: C - 29 September 1988; D - 13 March 1989; E - January 31, 1991; F - 19 November 1992

Projected SC L ife/DSN Support : 1 0 years/lO years

P-: Goddard Space Flight Center (GSFC)

Source: SIRD December 1982 Sponsor: OSSA

The Tracking and Data Relay Satellite System (TDRSS) consists of four identical satellites in geosynchronous orbits and a dedicated ground station. The first two satellites (TDRS east and TDRS west) will form the operational TDRS service providing near-global real-time user satellite coverage. The third satellite will be an in-orbit spare.

The payload of each TDRS is a telecommunications service system that relays communication signals between low Earth-orbiting user spacecraft and the TDRSS ground terminal. This relay is accomplished by two types o f communications links: (1) a multiple-access system, with one 30-element S-band phased-array antenna system; and (2) a single-access system, either S-band single-access or K-band single-access, with two 4.8-meter parabolic antennas, each operating at both S-band and K-band.

870-14, Rev. AF

B. FLIGHT PROFILE

Each TDRS will be placed into a geostationary orbit with an altitude of 35,800 km. At apogee, the satellites will arrive at 56, 79, 102, or 94 degrees west longitude corresponding to deployment and transfer from the Shuttle orbits of 8th descending, 9th descending, 10th descending, or 18th ascending nodes, respectively. From one of these initial locations, each TDRS will drift to its operational position, resulting in one TDRS at 41 degrees west longitude (TDRS east) and one at 171 degrees west longitude (TDRS west). Each spacecraft will have an inclination of 0 degree. The in-orbit spare will be located between 55 and 70 degrees west longitude at a 0-degree inclination to minimize the time needed to reach either geosynchronous station.

C. COVElXAGE

1. Coverage Goals

The DSN is responsible for supporting launch and transfer orbits and providing emergency support from Goldstone and Madrid beginning in February 1985. The 26- or 34-m antenna will provide the emergency support. Follow-on launch and transfer orbit support will be required for replacement launches from all three complexes.

2. Network Support

12 14 15 16 42 43 45 46 61 63 66

S-band TLM B P B P B P

S-band CMD B P B P B P

S-band TRK B P B P B P

NOTE: B = Backup; P = Prime (Launch support to ON stations)

Svstem nk ( M W Downlink (MHz 1 Polarization

S-band TRK 2035.96 2211.0 RCP

870-14, Rev. AF

Telemetry

Data Streams Format Subcarrier Frequency Bit Rate Record

Command

Support

Uplink Power Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rate Range Format Recording . Analog . Digital

1 PCM(NRZ-L) /PSK/PM 1024 kHz 250 or 1000 b/s Required

PCM/PSK/PM 2000 b/s 16 kHz

2 kW or 16 kW Ni 1 Not required Required Ni 1 Tone (Prime) , DSN standard (Backup)

Required Required f o r radio metric data in 34-m backup mode

I . * I . Phase Support Responsibility

STS Launch STDN Geostationary Orbit WSGT Erne rgency Support D SN

870-14, Rev. AF

43-4 . .

870-14, Rev. AF

ULYSSES

TDS Mgr: D. Enari NOPE: R. L. Rose

Project Mgr: W. Meeks MOM: P. Beech (ESOC)

LV/Bange: STS-IUS-PAM-S/ETR

Launch Date: October 6, 1990

Projected SC Life/DS N SUDDOrt : 8 years/5 years

P r o i ec t Re .mons ibilitv : Jet Propulsion Laboratory (JPL)/European Space Agency (ESA)

Source: SIRD December 1983 Sponsor: ESA/NASA Program Manager: R. Murray

The primary objectives of Ulysses are to extend scientific knowledge and understanding through exploration of the Sun and its environment, and to investigate possible mechanisms coupling solar variability to terrestrial weather and climate by studying the Sun's structure and emission as a function of latitude from the solar equator to the solar poles.

B. FLIGHT PROFILE

Ulysses consists of a single European Space Agency (ESA) spacecraft. The spacecraft will be launched in 1990 from Kennedy Space Center (KSC) by a Space Transportation System (STS) vehicle using an Inertial Upper Stage (IUS) and a Propulsion Assist Module (PAM-S) to inject the spacecraft into an interplanetary orbit toward Jupiter. After Jupiter flyby, the spacecraft travels

870-14, Rev. AF

in a heliocentric, out-of-ecliptic orbit with high heliographic inclination. The mission terminates in September 1995 at the end of the second polar pass. The highest priority portion of the mission occurs when the spacecraft is greater than 70 degrees heliographic latitude during solar passes.

C. COVERAGE

1. Coverage Goals

The antenna coverage profile provided below supports the Ulysses SIRD, JPL D-292, dated April 24, 1989. There have not been any additions or deletions to the SIRD since launch, October 1990. The requirements are expected to increase only when the project cannot obtain minimal support to retrieve data from its on-board tape recorder to complete daily 24-hour coverage throughout the prime mission phase.

The DSN expects to meet the coverage goals except when other spacecraft emergencies occur or in the case of other interruptions which are beyond the control of the DSN.

. . Phase (30 days)

Period Passes/Month Antennas

Launch 10/5/90 - 10/23/90 6 26-m

(TCMs, S/C checkout, and 90 science turn-on, calibrations) DOR during overlaps only L +41 to L +50

34 STD 8 70-m

27 34 HEF

Routine 12/90 30 34 STD

First Opposition 12/90 - 01/91 (70-m last week of D e c / first week of Jan)

Routine

First Conjunct ion

Routine

01/91 - 05/91 06/91 - 11/91 06/91

12/91 - 01/92

27 70-m

30 34 STD

39 34 STD

30 34 HEF

30 70-m

45 70-m

30 70-m

30 34 STD

870-14, Rev. AF

. . ission Phase

Jupiter Flyby

(30 days) Period Passes/Month Antennas

02/92 90 34 STD

02/92 30 70-m

Second Opposition 03/92 Gravitational Wave Exp . 03/92

34 STD

34 HEF

Rout i ne 04/92 - 05/92 30 34 STD

Second Conjunction 06/91 - 08/92 13 34 STD

06/92 - 08/92 17 70-m

09/92 30 70-m

10/92 - 11/92 13 34 STD

10/92 - 11/92 17 70-m

Routine 12/92 - 02/93 (to mid Feb)

Third Opposition 02/93 - 03/93 Gravitational Wave (from mid Feb) Exp . 02/93 - 03/93

30 34 STD

34 STD

34 HEF

Rout ine 04/93 - 05/94 30 34 STD

Solar Pass 1 06/94 - 08/94 30 34 STD

Routine 09/94 - 05/95 30 34 STD

Solar Pass 2 06/95 - 09/95 30 34 STD

EOM 10/95

2. Network Support

12 14 15 16 42 43 45 46 61 63 65 66

S-band TLM P P * P P * P P *

X-band TLM P P P P P P P P P

870-14, Rev. AF

Cruise S-band CMD P P * P P * P P *

S-band TRK P P * P P * P P *

NOTES: P = Prime; * = 26-m S-band support for initial acquisition or backup

During the first solar pass (May 1994 - October 1994) and the second solar pass (May 1995 - September 1995), the spacecraft will be in nearly continuous view of the southern hemisphere station, and then it will be in nearly continuous view of the northern hemisphere station.

12 14 15 16 42 43 45 46 61 63 65 66

S/X-band TLM P P P P P P P P P

Critical S-band CMD P P

S/X-band TRK P P Events

NOTE: P = Prime

MIL 71 and the compatibility test van will support compatibility and other project re-tests beginning in April 1990.

Svstem Uplink (MHzl Downlink (MHz L Polarization

S-band TLM -- 2293.148148 RCP

X-band TLM -- 8408.209876 RCP

RCP S-band CMD 2111.607253 --

S-band TRK 2111.607253 2293.148148 RCP

X-band TRK -- 8408.209876 RCP

870-14, Rev. AF

(1) Telemetry

Data Streams Format Subcarrier Frequency Bit Rate Record

(2) Command

(3) Support

1 (S- or X-band) PCM (NRZ-L) /PSK/PM 65.536 kHz for 64, 128, 256, 512, 1024, 2048, 4096, 8192 b/s 131.072 kHz for 2048 to 8192 b/s DODR required

PCM/PSK/PM 15.6250 b/s 16 kHz

up to 20 kW (34-m), 100 kW (70-m) Sidereal, except at launch Not required First pass (26-m, only) Moderate, except first pass Standard DSN

Support Responsibility I . .

STS Launch TDRSS IUS/PAM-S Injection TDRS S /USAF Cruise/Encounter/Solar Passes DSN

870-14, Rev. AF

(This page intentionally l e f t blank.)

870-14, Rev. AF

UPPER ATMOSPHERE RESEARCH SATELLITE

(UARS)

(Emergency Support)

Project Mgr: V. Moore (GSFC) MOM: S. Osler (GSFC)

LV/Range: STS/ETR

Launch Date: September 26, 1991 *o-~ecte ~. C J,ife/DSN Su~port: 1.5 years/l.5 years

Project Responsibilitv: Goddard Space Flight Center (GSFC) * . .

Source: SIRD June 1983 Sponsor: O S 0

The UARS project is designed to study the Earth's middle and upper atmosphere.

B. FLIGHT PROFILE

The UARS satellite will be launched from the ETR in 1991 via the STS shuttle. It will be placed directly into a circular orbit of 600 km x 600 km x 57 degrees. Its period will equal 97 minutes.

-3 45-1

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

Coverage will be provided by the DSN for UARS emergencies that would prevent communications via the normal channel of TDRSS to White Sands. Emergency support would be provided by the DSN 26-meter subnetwork of stations.

2. Network Support

SYstem Goldstone Canberra Madrid

12 14 15 16 42 43 45 46 61 63 66

S-band TLM

S-band CMD

S-band TRK

NOTE: E = Emergency

S-band TLM -- 2287.5

-- S-band CMD 2106.4

S-band TRK 2106.4 2287.5

(1) Telemetry

Data Streams Format Subcarrier Frequency Bit Rates Coding Record

1, 32, or 512 kb/s

870-14, R e v . AF

(2) Command

F o r m a t B i t R a t e S u b c a r r i e r Frequency

( 3 ) Support

U p l i n k P o w e r A n t e n n a R a t e A n t e n n a A n g l e D a t a A n t e n n a A u t o t r a c k D o p p l e r R a t e s R a n g e F o r m a t R e c o r d i n g . A n a l o g . D i g i t a l

PCM (NRZ-L) PSK/PM 1 kb/s , 0.i25 kb/s 16 ,000 Hz

TBD Moderate R e q u i r e d R e q u i r e d Moderate TBD

R e q u i r e d

870-14, Rev. AF

ER INTERSTELLAR MISSION (VIM)

TDS M g r : H . Cox NOPE: L . Shaw

P r o j e c t M g r : G. Textor Mission Di rec to r : R. Rudd

Launch: VGR-1 Sep t . 5, 1977; - VGR-2 A u g . 20, 1977

P r o j e c t e d SC Life/DSN Suopo r t : 2019

P r o i e c t R e s p o n s i b i l i t v : Jet Propuls ion Laboratory ( J P L ) * . .

Source: D r a f t SIRD November 1989 Sponsor: O S 0

The c o n t i n u a t i o n of t h e Voyager P r o j e c t beyond t h e o u t e r p l a n e t s i s c a l l e d t h e Voyager I n t e r s t e l l a r Mission and u t i l i z e s both Voyager spacecraft f o r t h e p e r i o d from January 1, 1990 through December 31, 2019.

B. FLIGHT PROFILE

The Voyager I n t e r s t e l l a r Mission o b j e c t i v e s w i l l be accomplished by ex tending o p e r a t i o n of bo th Voyager 1 and Voyager 2 throughout t h e approved mission p e r i o d .

The g e n e r a l mission o b j e c t i v e s of t h e V I M are:

(a) T o i n v e s t i g a t e t h e i n t e r p l a n e t a r y and i n t e r s t e l l a r m e d i a , and t o c h a r a c t e r i z e t h e i n t e r a c t i o n between t h e t w o .

(b) To cont inue t h e s u c c e s s f u l Voyager program of u l t r a v i o l e t astronomy.

870-14, Rev. AF

C. COVERAGE

1. Coverage Goals

The Project requires a minimum of 16 hours per day of tracking coverage for each spacecraft in order to obtain science telemetry data. The total station coverage requirements (both spacecraft combined) are set forth in Table 1. When the heliopause is reached (possibly in 2010), continued 70-m coverage of both spacecraft is required for the duration of the investigation.

Table 1 Ground Aperture Coverage Requirements (passes/week, both spacecraft combined)

Aperture Mandatory Enhancement

Function S TD HEF array STD HEF array

34mb 34mb 70m 34/70 34ma 34ma 70m 34/70

Telemetry , Doppler

and VGR-2 BLF Ranging, Command, 3 0 1.3 0 1 0 1 0

Telemetry Only 7 10 1 4 Yr 1 2 0

a. Assumes 10 hours per pass, exclusive of pre- and post-pass calibrations. b. 70m passes may be substituted.

870-14, Rev. AF

2. Network Support

Svstem Goldstone

1 2 1 4 1 5

S-/X-band TLM P P P

S-band CMD P P

S-/X-band TRK P P

Canberra

42 43 45

Madrid

6 1 63 65

NOTES: 1. P = Prime 2. DSS 12, 42, 6 1 tracking data are Doppler only, no ranging.

Svstem

Vovaaer 1:

S-band TLM

X-band TLM

S-band CMD

S-band TRK

X-band TRK

Vovacxer: S-band TLM

X-band TLM

S-band CMD

S-band TRK

X-band TRK

UDlink (MHz) Downlink ( M m

2114.676697

2113.312500

2296.481481

8420.432097

2296.481481

8420.432097

2295.000000

8415.000000

2295.000000

8415.000000

Polarization

870-14, Rev. AF

(1) Telemetry

Data Streams Voyager 1

Voyager 2

1 X-band, continuous and 1 S-band, selected periods 1 X-band, continuous and 1 S-band, selected periods

Format PCM(NR2-L) /PSK/PM Subcarrier Frequency 22.5, 360 kHz Bit Rate 40, 46.6, 80, 160, 600, 1200, 1400,

Record Dual telemetry ODRs required for 2800, 3600, 4800, and 7200 b/s

critical passes, single ODRs otherwise

Coding Convolutional, K = 7 R = 1/2

(2 ) Command

Format PCM (Manchester encoded) /PSK/PM Bit Rate 1 6 b/s Subcarrier Frequency 512 Hz

( 3 ) Support

Uplink Power

Antenna Rate Antenna Angle Data Antenna Autotrack Doppler Rates Range Format Recording . Analog . Digital

20 to 400 kW (400 kW for emergencies) S ide rea 1 Not required Not required Moderate Standard DSN

Interstellar DSN

870-14, Rev. AF

APPENDIX A

DSN ADVANCED PLANNING MISSION SET

Table A-1 is a compilation of potential future missions and is for information purposes only. Mission titles, new start dates, and launch dates are projected only.

Table A-1. Potential Future Missions

Projected

New Launch Mission Title Start Date Description/Purpose

Main Belt Asteroid FY TBD Late 1996 Asteroid Rendezvous would Rendezvous occur in late 2001. This

mission should be supportable from the 34-meter HEF and 70-meter subnets.

Lunar Geoscience FY TBD Late 1995 The spacecraft will be Observer (LGO) placed into a circular

lunar polar orbit obtain- ing telemetry via tape recorders. Primary orbital operations will last one year followed by extended mission operations. DSN 34-meter STD support is required.

Magnetic Field FY TBD 1994 The purpose of the NASA/ Explorer/Magnolia CNES coorperative mission

is to measure the changes in the Earth's magnetic field. Near circular, 86-degrees inclination orbit around Earth at altitude of 600 km. Five-year lifetime. S-band NASA standard transponder. Tape recorder data dumps twice per day to 26-meter subnet. Command, telemetry, and radiometric data required.

870-14, Rev. AF

Table A-1. Potential Future Missions (Continued)

Projected

Mission Title New Launch Start Date Description/Purpose

Orbiting VLBI FY TBD 1995 The experiment would (TDRSS Experiment) utilize some spare time

on a TDRSS satellite to look at a quasar simultaneously with an Earth-based telescope.

Cluster (ISTP - FY TBD Dec. 1995 This ESA mission consists Multipoint) of four spacecraft in an

eccentric polar orbit to provide a three- dimensional study of plasma turbulence surrounding the earth. Support would be from the ESA 15-meter and DSN 26-meter subnets.

Infrared Space Obser- FY TBD 1993 3rd The Infrared Space Obs- vatory (IS01 Quarter servatory (ISO) mission

is scheduled for an Ariane 4 launch in the 3rd quarter of 1993. The spacecraft will be placed in a 70,000-km by 1000-krn orbit (24-hour orbit) and will be three-axis stabilized. The instruments will be cooled to approximately 3 K with liquid helium. The expected lifetime is 18 months (the amount of time to deplete the liquid helium to the point where the instruments become inoperable). The spacecraft has no on- board recording, and therefore the spacecraft must be tracked continuously to recover the science data in real

870-14, Rev. AF

Projected

New Launch Mission Title Start Date Description/Purpose

IS0 (Continued) time. The data rate is 32 kbps, convolutionally coded at rate 1/2 and with a constraint length of 7. Goldstone is the only DSN location required, and the expected coverage from the Goldstone 26-m tracking station is requested at a level of 8 to 10 hours per day. Two-way Doppler and range are the metric data requirements.

Orbiting Maneuver Mid-1990s TBD The OMV project is spon- Vehicle ( o w ) sored by Marshall Space

Flight Center (MSFC) . The purpose of this project is to augment the capabilities of the Shuttle and the space station by providing a remotely piloted space structure that deploys, services, and/or retains orbital objects for the manned vehicle.

Radioast ron FY 89 April 1995 Radioastron is a proposed cooperative mission with the Soviet space agency IKI. The spacecraft is to be placed in a high elliptical orbit and is designed to perform space-based VLBI in conjunction with Earth- based radio telescopes. Mission life time is expected to be two years.

870-14, Rev. AF

Projected

Mission Title New Launch Start Date Description/Purpose

VSOP (MUSES-B) FY 90 Mid 1995 VSOP is a proposed cooperative orbiting VLBI mission conducted by the Japanese Space agency ISAS. The mission is planned as a three-phase mission with a joint Japan-U.S. phase, a Japanese stand-alone phase, and a U. S . standalone phase, The VLBA network is expected to participate.

870-14, Rev. AF

APPENDIX B

GLOSSARY

Apogee Kick Motor

Automatic Nutation Control

Attitude Propulsion System

Astronomical Unit

Charge Composition Explorer

Command and Data Processing Facility

Canberra Deep Space Communications Complex

Goldstone Deep Space Communications Complex

Geomagnetic Tail

Institute of Cosmic Research (USSR)

Interplanetary Monitoring Platform

Ion Release Module

Inertial Upper Stage

Kagashima Space Center (ISAS Launch Site, Japan)

Launch and Early Orbit Phase

Madrid Deep Space Communications Complex

Mission Operations Manager

Mission Support Manager

Network Director

Network Support Manager

Shuttle POCC Interface Facility

Tanegashima Space Center (NASDA launch site, Japan)

Telemetry

Tracking

Telemetry, Tracking, and Command

870-14, Rev. AF

010-14, Rev. AF

APPENDIX C

DEFINITIONS OF TERMS

The definitions listed here are in the order of mission development.

Approved Mission A mission established as having new-start approval or having been appropriately obligated.

Reimbursable Mission Mission for which DSN support costs are reimbursed to NASA by various users (e.g., U.S. private corporations, other foreign and domestic agencies).

Compatibility Testing To demonstrate compatibility of spacecraft systems with supporting network elements.

Launch and Early Orbit a. For geosynchronous missions, launch through the completion of AKM firing, with sufficient time to compute the resulting orbital parameters.

b. For nongeosynchronous missions, launch until orbital parameters have been computed, not to exceed 24 hours.

Parking Orbit

Transfer Orbit

Drift Orbit

Mission Orbit

Halo Orbit

A preliminary orbit into which a spacecraft is injected prior to maneuvers placing the spacecraft into its mission orbit or intermediate orbit.

An intermediate orbit into which a spacecraft is placed prior to its final mission orbit. Generally, this orbit is to raise the spacecraft apogee.

An orbit with an orbital period of slightly more or less than one sidereal day and which allows for a spacecraft longitudinal position to be changed.

That orbit into which a spacecraft is placed for the purpose of meeting mission objectives.

A special type of periodic orbit about an equilibrium point between two celestial bodies in a plane generally normal to the plane of the line of sight between the two bodies.

870-14, Rev. AF

DEFINITIONS OF TERMS (cont)

Geosynchronous/ A spacecraft in Earth orbit with a period of one Geostationary Satellite sidereal day is considered geosynchronous. If

its eccentricity and inclination approach zero, the satellite is further defined as geostationary.

Sun-synchronous

Contingency Support

Backup Support

A type of orbital condition, typically between 80 and 120 degrees inclination, where the ascending node crosses the equator daily at a specified local Sun time.

A support situation, which Network resources may be scheduled on short notice to provide support requirements in case of spacecraft functional or mission operational anomaly.

A support readiness condition in which stations may be scheduled to assume mission support responsbilities should assigned primary support elements require augmentation or replacement.

870-14, Rev. AF

APPENDIX D

FACILITY IDENTIFIERS

Goldst one D S S 12 34-m S-/X-band antenna DSS 14 70-m S-/X-band antenna DSS 15 34-m S-/X-band high-efficiency antenna DSS 16 26-m S-band antenna D S S 17 9-m S-band antenna

Canberra D S S 42 34-m S-/X-band antenna DSS 43 70-m S-/X-band antenna D S S 45 34-m S-/X-band high-efficiency antenna D S S 46 26-m S-band antenna

Madrid DSS 61 34-m S-/X-band antenna DSS 63 70-m S-/X-band antenna DSS 65 34-m S-/X-band high-efficiency antenna DSS 66 26-m S-band antenna

CDSCC Canberra Deep Space Communications Complex, Australia GDSCC Goldstone Deep Space Communications Complex, California MDSCC Madrid Deep Space Communications Complex, Spain

CTA-21 Compatibility Test Area

MIL-71 Merritt Island Launch

NOCC Network Operations Control Center

870-14, R e v . AF

870-14, Rev. AF

DISTRIBUTION LIST

Contact L. McKinley (mail address 303-404, ext. 4-0061) regarding changes to this list.

Organization Name

230 250 260 280 310

Downhower, W. McKenzie, M. Momjian, E. Seidel, D. M. Burke, E. S. Gatz, E. Linick, T. D. Ausman, N. E. McKinley, E. L. Textor, G. P. Meeks, W. G. Chang, D. Ellis, J. Erickson, K. D. Goltz, G. Holladay J. A. Jordan, J. F. MacMedan M. L. McDanell , J. P . Matousek, S. Tan, K. Taylor, R. E. Bishop, D. Black, C. A. Dickinson, R. M. Garrison, G. Gevargiz, J. Green, R. R. Hersey, D. Horton, T. R. Kantak, A . Kushner, L. Matousek, S. Peng, T. Robbins, P. Royden, H. N. Ruggier, C. J. Rydgig, R. Verish, R. Wilhelm, M. Bricker, C. Brunder, G. Carlton, M. Ellman, A. F. Johnson, G. Josephs, R. H.

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

Hail Code

180-900 180-900 180-900 180-205 180-404 2 64-7 4 7 180-404 2 64-4 19 264-627 17 1-245 264-456 301-345 301-125 301-235 264-201 264-747 301-230 233-208 301-125L 301-14OL 264-828 264-728 161-228 303-403 238-540 238-540 161-228 238-540 161-228 161-22 8 161-228 144-201 301-14OL 161-228 161-228 F1129 161-22 8 150-300 150-302 161-228 301-375 301-480 301-375 125-16119

%- 301-360 301-480

360 (Contd)

870-14, Rev. AF

DISTRIBUTION (Continued)

Kardell, D. Kirnball, K. R. Missman, P. Osmond, J. Rodr igue s Stinnett, W. Thornton, T. H. Caticchio, A. Cureton-Snead, I. Davis, E. K. Durham, R. Grant, H. M. Guyton, S. L. Hampton, E. Jenni,ngs , L . E. Lacey , N . Ryan, R. E. Taylor, T. M. Custer, D. Dumas, L. N. Mallis, K. P. Posner, E. C. Stevens, R. Westmoreland P. T. Whyman, E. F. de Groot, N. F. Hall, J. R. Layland, J. W. Martin, W. L. McLaughlin, F. D. Stelzreid, C. Wilcher, J. H. Bailey , M. Black, C. A. Bryan, A. I. Burt, R. Falin, B. Garcia, E. Liewer, K. McAndrew , W . F . McClure, J. P. Perkins, R. Rogers, J. W. ROSS, D. L. Thom, E. H. Tran, T. L. Vegos, C. Wackley, J. A. Wallace, R. J. Wick, M. R. Yeaman, D.

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

301-375 301-375 301-360 301-360 301-433 301-360 301-433 301-345 301-375 301-335 301-345 301-341 301-335 301-345 3 01-34 0 301-345 301-341 301-345 503-205 30 3-4 0 0 303-400 303-4 0 0 303-400 303-400 303-400 303-402 303-401 303-401 303-402 303-401 303-402 303-402 3 03-403 303-403

303-403 303-403 303-403 303-403 303-403 303-403 303 -4 03 303-403 303-403 303-403 303-403 30 3-4 03 303-403 303-403 303-403 303-403

JPL/CAPE

0 r Gani z at ion

870-14, Rev. AF

Adams, J. F. morose, R. J. Baker, N. Batka, E. Berman, A. Beyer, P. Borncamp, F. Brown, S. Bruce, R. Carroll, D. Chang, A. F . Collins, L. Cox, H. G. Delgado, C. Dillard, D. Doggett, J. DSN Document Center Durkee, D. Elliano, L. Enright, S . Enari, D. M. Erwin, W. Espinueva, R. Fanelli, N. Gillette, R. Goodwin, J. P. Gould, G. D. Gugel, R. Herndon, W. M. Hodde r , J . Hollingsworth, R. Howe, T. Hoynes, C. Issa, T. Johnson, J. L. Johnston, D. W. Jones, J. Keller, W. Knight, A. Knight, A. G. Krueger, W. J. Kuhn, T. Landon, A. Luers, E. B. Martindale, B. Martinez, G. McCluskey, J. McKinley, L. Millard, T. A. Milligan, J.

Quantity

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 10 1 1

Mail Code

507-105 303-404 1 2 5-B17 507-120 303-404 30 3-4 0 4 303-404 507-215 230-109 230-109 303-404 507-120 303-404 503-102 507-120 3 03-4 0 4 503-147 507-120 507-120 507-215 303-404 507-215 507-120 303-404 303-404 303-404 507-105 507-120 230-109 303-404 507-120 507-120 507-215 507-105 507-215 303-404 507-120 507-120 507-120 507 - 2 1 5 507-2 1 5 303-404 507-120 303-404 DSCC-61 507-120 507-120 303-404 DSCC-07 507-215

Organization

440 (Contd)

Goldstone

870-14, Rev. AF

Mudgway, D . Nad jarian, R. Network Operations Library

Nevarez , R. Nguyen, V. Q. Norton, R. L. 0 ' Connor, R. Osoro, J. Owen, E. Patterson, T. Pennington, D. Price, T. D. Riddle, F. M. Rogers, G. D. Rose, R. Roth, R. Rouse , M. Salazar, A . Shaw, R. Short, A. Soliday, L. D. Spear, R. Tipton, L. Tong, J. Torres, R. Traxler, M. R. Tucker, W. Von Delden, D. E. Waldherr, S. Walsh, E. Winn, G. Wiseman, R. Wolf, S. R. Wolken, P. Wyatt, M. Butcher, L. Gaudian, B. A . Jerscheid, J. McPartland, J. E. Mischel, D. Sturgis, L. Klein, M. J. Kolden, J. R. Renzetti, N. A . Cramer, J. A . Miller, J. A . Roberts, J. A . Chandlee , R. Riet hle , G .

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

m i l Code

303-4 0 4 303-404 230-101

507-120 12 5-B17 507 -215 507-120 507-120 507-120 12 5-B17 507-215 503-105 502-600 507-105 5 0 7-12 0 507-215 507-120 303-404 125-B17 507-120 230-109 125-B17 12 5-B17 507-215 507-120 303-404 507-120 303-404 507-120 303-404 30 3-4 0 4 507-215 507-120 507-120 303-404 DSCC/33 DSCC/ 33 DSCC/39 DSCC/37 DSCC/61 DSCC/25 303-401 303-401 303-401 72-112 83-204 72-112 111-150 111-150

ani7at i on

750 860 900 MDSCC CDSCC

870-14, Rev. AF

Miller, R. B. Weber, W. J. Rea, D. G.

c/o Latham, R. S .

NASA Headqua r t e r s Washington, D.C. 205 46

Bohlin, D. Carl t on , J . Chang, J. Donivan, F. Fahnestock, R. J. Ferrick, E. Fitts, G. Fit zge rald , M . Force , C . Fosque , H . Greaves, J. Hornstein, R. M. Hornstein, R. S. Johnston, D. Kelley, J. D. Knotts , A. Lacurto, J. Matlick, T. L. McLaughlin, J. Miller, A. Rice , D . Shaw, J. Sobala, J. Strobel, G . Struba, D. Theiss, H. Ticker, R. L. Willett, J. Winbush, W.

Australia NASA Representative Director, Administration

Deputy Executive Director and Finance

Madrid NASA Representative INTA

Colonna, R. Dunn, J. (c/o Latham, R. S.) Boyd, J.

South, J. Gopequi , L . (c/o Latham, R. S.)

1 1 1 4 4

1 1 1 1 1 1 1 2 1 1 1 3 1 1 1 1 1 1 1 1 1 2 1 1 1 1 1 1 1

100-22 180-701 180-701

303-404

S D-1 oc OT OT ox 0 BRB 0 OP SE OT ox os OT oc oc oc LIC-17 0 os L-2 os SL os OT OT ss OT

PO 303-404

303-404

870-14, Rev. AF

ua.m€i t i t v

NASA Goddard Space F l i g h t Center Greenbel t , MD 2 0 7 7 1

Blaney, K. Boeckel, J. Bullock, G. B u r r , P . T . B u t l e r , T . Dol l , C. Fahnestock, D. Jackson, J. Jones, A. Jones , C. Joyce, J. B. Klineberg, J. M. Levine , A. L e w i s , L . H. L ight foot , P . Long, R. Lorenz, B. T . Mack, W. F. McKenzie, J. Ousley, G. Young, E . N. Richon, K . Sizemore, K . S t an ley , R. T e l e s , J. Woodruff, J .

Johnson Space Center Houston, TX 77058

McDonald, K .

John F. Kennedy Space Center Nat iona l Aeronaut ics and Space Adminis t ra t ion Kennedy Space Center , F . 32899

D i l l e r , G. Jenkins , G. T .

2 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

Centre Nat iona l d 'Etudes S p a t i a l e s (CNES) Cent re S p a t i a l D e Toulouse 1 8 A venue Edoua r d - B e l l ' n , 31055 Tou louse . Cedex, France

1 Code

480.0 700.0 602.0 1 0 0 * 0 540.0 554.0 500.0 554.2 300.0 602.0 553.1 1 0 0 * 0 534.2 533.0 514.0 405.0 533.0 301.0 501.0 404.0 534.2 554.0 400.6 515.0 554.0 502.0

DC-NIP0

P-A-T1B GUSP

DP/OPS Trebaol, J. 3

870-14, Rev. AF

D I S TRI BUT I ON (Continued)

Organization &me titv

Embassy of France, Scientific Mission c/o Attach6 for Space Affairs 4 1 0 1 Reservoir Road, NW Was-, D.C. 70007-2176

Laidet , L.

European Space Agency 6100 Darmstadt -

Wilkins, D.

German Space Operations Center (GSOC) Muncher Str. 2 0 8 0 3 1 Oberpfaffenhofen Post Wessling Federal Republic of Germany

Lame1 , G .

National Space Development Agency (NSDA of Japan)

Daichi Daimon Bldg. Miato - ku. Tokvo 1 0 5

Horii 2

Nishimura, T. 1 Director of Usuda Deep Space Center Institute of Space and Astronautical Science

3-1-1 Yoshinodai, Sagamihara-Shi Kanagawa - Ken. 229 - Japan

(ISAS of Japan)

cs TC /VOI AFSCF/ROSR P.O. Box 3430 ONIZUKA AFB -

Hall, A.

Bendix Field Engineering Corp. One Bendix Road

la, MD 2 1 0 4 5

Central Library Conrad, J. Hampt on , M.

1 Library/COL 4 SEG/COL 2 NAO/COL

8 7 0 - 1 4 , R e v . AF

D I S T R I BUT1 ON ( C o n t h u e d )

zat ion Hame

B e n d i x Field E n g i n e e r i n g C o r p . 1 0 2 1 0 G r e e n b e l t R d .

brook, MD 7 0 7 0 6 - 7 2 1 8

R I , I nc . 585 G r o v e Street Herndon. VA 2 2 0 7 Q

S tanford T e l e c o m m u n i c a t i o n s 2 4 2 1 Mission C o l l e g e Blvd. - NTIA 179 A d m i r a l C o c h r a n D r i v e A n n a p o l i s , ML, 21401

A l b i k e r , E G a l e , J. H e l m s , B. Hi tch, H. H u t t o , C . Johnson, P. K e i t h , E . L u t z , R. W e s t m o r e l a n d , P . NCC L i b r a r y NMOS L i b r a r y O f f i c e Manager P a u l u s , J. P r i n t y , C . Reamy, V. R h o d e r i c k , G. R u t l e d g e , R. B.

B o y d , D. B r y a n t , F.

D a v i e s , R .

R o b Haines

TDA D o c u m e n t a t i o n L i b r a r y V e l l u m F i l e s

1 1 2 3 1 1 1 4 2 5 2 1 1 1 2 1 1

MRT PM/ARO DOC/ARO NOG/ARO P A P / B l d g . 1 6 PM 310 P RG / ARO NTO/ARO N C C / B l d g . 1 3 LIB/ARO MTO NTO /ARO

SEAS DSO/ARO

PM/ARO MRTG

111-150 lll-B25

870-14, Rev. AF

Stanford Telecommunications 1761 Business Center Drive Suite 400 -

Benjamim, T. Kosmann, W.

Computer Science Corporation 4600 Powdermill Road Reltsvale, MD 70705

ITT Research Institute 185 Admiral Cochrane Drive Annapolis, MD 21401

NASA/GSFC/WFF Bldg. N162 Wallops Island, VA 2333 7

Frazier, W. Solomon, H.

Pfeifer, R.

Grant, D.

MSFC Bldg. 4654, Room 103

tsville, Ab 3 5 8 U

Ward, T. H.

c-122 D-512

870-14, Rev. AF

The following names receive the small version of this document.

100 310 330 360

401 430

Reid, M. Smith, J. G. Kovatch, P. Crowe, R. Humphrey, G. Durham, R. Hermsen, D. Gero, M. A. Rogers, W. Westmoreland, P. Adams, J. F. Amorose, R. Batka, E. Beyer, P. E. Cox, H. Crowfoot, E. Dillard, D. Dreher, B. Erwin, W. Espinueva, R. Gaudian, B. A . Gugel, R. Hall, G. Hodder, J. Hollingsworth, R. Howie, B. Keller, W. Knight, A . Landon, A . Martinez, G. McCluskey, J. McKinley, L. McPartland, J. E. Mischel, D. Nevarez, R. O'Connor, R. Osoro, J. Rose, R. Rouse, M. Shaw, L. Short, A. Tucker, W. Waldherr, S. Wolken, P.

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 5 1 1 1 1 1 1 1 1 1 1 1 1

180-904 303-402 150-300 301-360 301-360 301-345 179-206 303-400 303-403 30 3-4 0 3 507-105 30 3-4 0 4 507-120 303-404 303-404 D SCC/ 3 8 507-120 303-404 507 -12 0 507-120 DSCC / 3 3 507-120 DSCC / 3 9 507-120 507-120 507-120 507-120 507-120 507-120 507-120 507-120 303-404 DSCC/37 DSCC/61 507-120 507-120 50 7 -12 0 507-120 507-120 507-120 507-120 507-120 507-120 507-120

870-14, Rev. AF

Organization . NASA Headquarters Washingtan, D.C. 2 0 5 4 6

Cost rell, J . Fahnestock, R. Hornstein, R. Harris, D. Kelly, J. Stroebel, G. Ticker, R. L.

NASA Goddard Space Flight Center Greenbelt. MD 7 0 7 7 1

Hill, P. Guidice, V. Hensel , W. Lawless, E. Mansberg, G. Salzberg, I. Seiders, R. Turner, V.

NASA Ames Research Center Moffett Field. CA 94035

Fimmel, R. 0 . Lasher, L. E. Lozier, D. W.

NASA-Lewis Research Center 21000 Brookpark Road Cleveland, Ohio 44135

Quantity

Hollansworth, J. E. 1

Ford Aerospace Communications Corp. 7375 Executive PI. #400 Seabrook, MD 20706-2278

Danko , E. New, R. Pyle, J .

Computer Science Corporation 4600 Powdermill Road Beltsville. MD 70705

Mail Code

TN TN TN TX TN EL OT

542.2 521.2 542.3 542.1 542.1 542.0 501.0 540.0

244-8 244-14 244-8

502 500 502

Frazier, W. 1 c-122

870-14, Rev. AF

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